BEGIN:VCALENDAR VERSION:2.0 PRODID:-//wp-events-plugin.com//6.6.4.4//EN TZID:Asia/Jerusalem X-WR-TIMEZONE:Asia/Jerusalem BEGIN:VEVENT UID:0-30@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20140409T123000 DTEND;TZID=Asia/Jerusalem:20180409T143000 DTSTAMP:20230504T064526Z URL:https://aerospace.technion.ac.il/events/graduate-studies-research-day/ SUMMARY:Graduate Studies Research-Day DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Lobby of the m ain faculty building\n Zoom: \n Abstract: \n Details: Graduate students wi ll present their research projects and achievements. Everyone is invited t o the poster exhibits hosted by those student\, who will be also available to discuss their work and answer question. Several prizes will be awarded to best presentations.\nClick here to view photos taken during the event. \n CATEGORIES:Events LOCATION:Lobby of the main faculty building END:VEVENT BEGIN:VEVENT UID:0-18@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20140410T110000 DTEND;TZID=Asia/Jerusalem:20140410T120000 DTSTAMP:20221030T083401Z URL:https://aerospace.technion.ac.il/events/open-house-for-graduate-studie s/ SUMMARY:Open Day for Graduate Studies DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Library Classr oom (no. 165)\n Zoom: \n Abstract: \n Details: On April 10th the Aerospace Engineering faculty will hold an “open day” for graduate studies (M.S c. and Ph.D.). First and second degrees students from the Technion and oth er universities are invited to attend. Graduate students from the AE facul ty will be available as “guides”\, and faculty members will also take part in the day.\nProgram:\n11:00 gathering\n11:15 Words from the Dean\n11 :30 Words from the Graduate Students Representatives\n11:45 Presentation o f the Graduate Studies Center\n12:15 Q&\;A\n12:45 A light lunch\n13:30 Visits to the faculty labs\, personal talks with faculty members etc.\nFor further information\, please contact Ms. Shula Pachter\, Graduate Studies Office of the Aerospace Engineering faculty\, phone: 04-8293365\nWe look forward to seeing you!\n CATEGORIES:Events LOCATION:Library Classroom (no. 165) END:VEVENT BEGIN:VEVENT UID:0-24@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20140424T084500 DTEND;TZID=Asia/Jerusalem:20140424T170000 DTSTAMP:20221030T083402Z URL:https://aerospace.technion.ac.il/events/the-36th-israel-symposium-on-c omputational-mechanics-iscm-36/ SUMMARY:The 36th Israel Symposium on Computational Mechanics (ISCM-36) DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Facu lty\n Zoom: \n Abstract: \n Details: The department of Aerospace Engineer ing will host the 36th Israel Symposium on Computational Mechanics (ISCM-3 6). The Symposium consists of lectures of experts from academia and indust ry on the use of computers for computing solutions for problems of solid a nd fluid mechanics. The opening Invited Lecture will be given by the well known Prof. Anthony Patera from MIT\, who has invented Spectral Elements ( for fluid problems). See the enclosed program.\n CATEGORIES:Events LOCATION:Aerospace Faculty END:VEVENT BEGIN:VEVENT UID:0-27@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20141106T090000 DTEND;TZID=Asia/Jerusalem:20141106T170000 DTSTAMP:20221030T083403Z URL:https://aerospace.technion.ac.il/events/the-13th-israeli-symposium-on- jet-engines-and-gas-turbines/ SUMMARY:THE 13TH ISRAELI SYMPOSIUM ON JET ENGINES AND GAS TURBINES DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Facu lty Auditorium\, room no. 235\n Zoom: \n Abstract: \n Details: THE 13TH (B ar Mitva) ISRAELI SYMPOSIUM ON JET ENGINES AND GAS TURBINES will be held o n November 6th\, 2014 at the Auditorium of the department of Aerospace En gineering\, Technion\, (room 235).\nIt concerns the different topics assoc iated with the jet engine and gas turbine industry. The lectures will be p resented by top expert from Israel and abroad. The symposium will also inc lude a display of several Israeli-made jet engines and components.\nFor th e program of the symposium\, see here.\nThose who plan to attend the sympo sium (highly recommended...) and did not register yet\, are kindly request ed to do so using the attached form.\nLooking forward to seeing you in the symposium!\n CATEGORIES:Events LOCATION:Aerospace Faculty Auditorium\, room no. 235 END:VEVENT BEGIN:VEVENT UID:0-16@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20141211T180000 DTEND;TZID=Asia/Jerusalem:20141211T190000 DTSTAMP:20221030T083404Z URL:https://aerospace.technion.ac.il/events/auvsi-project-conclusion-and-p resentation-evening/ SUMMARY:AUVSI Project Conclusion and Presentation Evening DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Facu lty Auditorium\, room no. 235\n Zoom: \n Abstract: \n Details: The autonom ous airborne system\, designed\, built and flown by a joint team of studen ts from the faculties of Aerospace Engineering and Computer Science\, wil l be presented in the event.\n\n CATEGORIES:Events LOCATION:Aerospace Faculty Auditorium\, room no. 235 END:VEVENT BEGIN:VEVENT UID:0-535@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20141231T163000 DTEND;TZID=Asia/Jerusalem:20141231T173000 DTSTAMP:20230603T193539Z URL:https://aerospace.technion.ac.il/events/feasibility-study-of-a-mediuml ong-range-ramjet-cruise-missile/ SUMMARY:Feasibility Study of a Medium/Long Range Ramjet Cruise Missile DESCRIPTION:Lecturer:Avi Peker\n Faculty:Department of Aerospace Engineerin g\,\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The ramjet engine is an air-breathing engine that operates without the need of moving parts. This type of engine constitutes a simple and efficient way of propulsion. The use of a ramjet engine as a sustaine r of a cruise missile can be feasible because of its ability to deliver hi gh and constant thrust for long periods of time.\nThe present study deals with the external ballistics and flight performance and also with the inte rnal ballistics (propulsion unit) of a supersonic cruise missile.\nThe fir st part involves the missile structure and aerodynamic properties\, aerody namic heating and it effect on the design parameters and a 3DOF trajectory simulation of the missile. The internal ballistics study includes the ram jet/solid booster engine performance analysis where thrust\, specific impu lse and flow mass are derived as a function of altitude and flight velocit y. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-527@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150112T163000 DTEND;TZID=Asia/Jerusalem:20150112T173000 DTSTAMP:20230603T193312Z URL:https://aerospace.technion.ac.il/events/state-estimation-in-systems-wi th-random-coefficients/ SUMMARY:State Estimation in Systems with Random Coefficients DESCRIPTION:Lecturer:Daniel Sigalov\n Faculty:The Interdepartmental Program for Applied Mathematics\,\n Institute:Technion – Israel Institute of Te chnology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng .\n Zoom: \n Abstract: \n Details: \n State estimation in dynamical system s with randomly switching coefficients is an important problem with a var iety of applications. The most commonly met problems that are formulated  within the random coefficients state-space approach\, are maneuvering targ et tracking and fault-tolerant filtering. A related class of problems is r eferred to as data association or data ambiguity.\nIn this family\, the es timation process is further complicated by the fact that the acquired data  has uncertain origin. Typical applications include target tracking in cl utter and multiple target tracking.  In this talk we aim at deriving a u nified framework for state estimation problems under data and model uncer tainties. First\, we present the problem of tracking a maneuvering target restricted to perform a bounded number of maneuvers and show that\, despi te the inherent deviation from the standard Markov switching assumption u nderlying most state-of-the-art algorithms\, it may be reformulated and s olved using a generalized version of such tools. We proceed with an overv iew of linear minimum mean-square error (LMMSE) algorithms for state esti mation in systems with random coefficients. We show that the novel formul ation allows treatment of problems that have not been addressed in the LMM SE sense in the past. These include target tracking in clutter and multip le target tracking. Finally\, we present a general framework\, accompanie d by a variety of applications\, which allows a utilization of a single IM M-like algorithm to solve a variety of state estimation problems.  These include maneuvering target tracking\, clutter and data association\, multi ple target tracking\, tracking of splitting targets and more. In some case s it will be shown that the resulting unified IMM-like filter reduces to some classical algorithms such as PDA and JPDA. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-540@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150114T163000 DTEND;TZID=Asia/Jerusalem:20150114T173000 DTSTAMP:20230603T193708Z URL:https://aerospace.technion.ac.il/events/critical-examination-of-functi onal-decomposition-and-morphology-as-an-engineering-design-teaching-method / SUMMARY:Critical Examination of Functional Decomposition and Morphology as an Engineering Design Teaching Method DESCRIPTION:Lecturer:Michael Press\n Faculty:Department of Aerospace Engine ering\,\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n Engineering design is a highly complex cognitive proces s of solving problems by developing new solutions and products. In the pas t this process was accomplished using intuition and experience\, until a r ealization came that a methodology must be developed in order that novice designers could produce good solutions. One of the methods was developed i n Germany by Pahl and Beitz\, who attempted to answer the need by introduc ing the Systematic Design methodology\, also known as the Rational Model. At the heart of the rational model lies the Functional Decomposition and M orphology (FD&\;M) method for the phase of conceptual design. Nowadays\ , FD&\;M is the most popular method taught in engineering schools.\nThe present research investigates the FD&\;M method in educating engineers through an experiment conducted on students (N=29) in the faculty of aero space engineering. Participants were both undergraduate and graduate stude nts. The application of the method was studied in analyzing an existing de vice and for the purpose of new product design. The research was based on analysis of design reports in the form of submitted homework assignments a nd of a self-reflection questionnaire that was generated for the purpose o f the research. The investigation revealed many difficulties and shortcomi ngs of the FD&\;M method\, classified into 10 different problematic asp ects that were recognized and demonstrated. The analysis indicated that th e method is quite difficult to apply\, is non-intuitive and most of the ti me is a hindrance to innovation. The results also showed that the method i s much more complicated than initially perceived by students. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-532@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150119T163000 DTEND;TZID=Asia/Jerusalem:20150119T173000 DTSTAMP:20230603T193448Z URL:https://aerospace.technion.ac.il/events/the-physics-of-centipede-micro droplet-generation/ SUMMARY:The Physics of 'Centipede' Microdroplet Generation DESCRIPTION:Lecturer:Dr. Michael Chemama\n Faculty:School of Engineering an d Applied Sciences\, Harvard University\,\n Institute:USA\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n We explore the physics behind high-throughput devices for the production of monodisperse microdroplets. Microdroplets are used more and more in a wide variety of applications: to conduct chemical reactions in picoliter volumes\, as biological screening assays or as templates to prod uce calibrated microparticles and microcapsules of active ingredients. The accuracy of the screening assays as well as the degree of control over th e chemical reactions and the release kinetics of active ingredients critic ally depend on a very narrow size distribution for the microdroplets. In a ddition\, a very large number of drops is required. Unfortunately\, tradit ional high throughput methods offer limited control over the drop size.\nI n 2013\, the Weitz laboratory at Harvard University introduced a robust de vice that produces monodisperse drops at a high throughput. This device\, called centipede because of its hundreds of parallel channels\, allows the use of microdroplets for a much broader range of applications. A single d evice takes up a volume of 100 mm3 and can produce up to 150mL/h of monodi sperse microdroplets: size variations remain below 3%. In this talk we exp lain the mechanism through which it produces droplets in order to understa nd how the droplets' size is related to the device’s design parameters a nd what the limiting throughput is. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-541@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150121T163000 DTEND;TZID=Asia/Jerusalem:20150121T173000 DTSTAMP:20230603T193746Z URL:https://aerospace.technion.ac.il/events/experimental-and-theoretical-i nvestigation-of-the-guidance-system-of-an-exo-atmospheric-kill-vehicle/ SUMMARY:Experimental and Theoretical Investigation of the Guidance System of an Exo-Atmospheric Kill Vehicle DESCRIPTION:Lecturer:Vladimir Kurovsky\n Faculty:Department of Aerospace En gineering\,\n Institute:Technion – Israel Institute of Technology\n Loca tion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Ab stract: \n Details: \n One of the defense methods against ballistic missil es threat is to intercept them at the mid-course phase\, which is a part o f the ballistic trajectory that lays in space. At high altitude or in spac e\, an interceptor missile can be guided by moving the main motor nozzle\, known as TVC (Thrust Vector Control) or by reaction jets. Usually\, space interceptors are not equipped with explosive warhead\; therefore\, a hit- to-kill collision is required.  For this reason\, a TVC control may not b e sufficient because of its non-minimum phase feature\, which increases th e interceptor time constant. Therefore\, in the last few seconds before th e “end-game”\, it is best to maneuver using forward reaction jets guid ance or a combination of forward and tail reaction jets.\nThis research pr esents a theoretical and an experimental investigation of the solid propel lant based reaction jets guidance system for an exo-atmospheric intercepto r (kill vehicle). In the first part\, a theoretical model of the system wi th a number of interceptor versions and reaction jets system was built and solved numerically. The reaction jets and interceptors performance was in vestigated using a computer simulation\, integrated in a proportional navi gation (PN) guidance loop. In the second part of the research\, an experim ental system was designed and built\, whose purpose is to demonstrate the work of the reaction jets system and to measure its thrust\, response time \, internal pressure and temperature conditions. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-528@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150128T163000 DTEND;TZID=Asia/Jerusalem:20150128T173000 DTSTAMP:20230603T193333Z URL:https://aerospace.technion.ac.il/events/rapidly-exploring-random-trees -for-guidance-of-autonomous-vehicles/ SUMMARY:Rapidly Exploring Random Trees for Guidance of Autonomous Vehicles DESCRIPTION:Lecturer:Sharon Yasovitch\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n The rapidly-exploring random tree (RRT) method was des igned for guidance of a robotic vehicle by performing a random sampling se arch that generates feasible paths while taking into consideration constra ints such as obstacles. The method generates fast solutions for a given pr oblem and improves them by adding more and more samples to the tree\; howe ver\, it tends to converge to solutions that are far from optimal. A varia tion of the RRT method\, known as RRT*\, was recently designed to generate solutions that almost surely converge to the optimal solution. However\, it requires a substantially larger computation effort.\nCurrent RRT based algorithms plan the motion of the vehicle while obstacles are presumed sta tionary and the goal target is at a fixed position. A new variant for RRT is proposed for dealing with time-dependent problems. Dynamic environments that include changes of goal target\, constraints\, and system dynamics o ver time can be considered by this variant. Results show convergence to mi nimal time solutions when based on a simple RRT method\, without the need for complicated schemes like the RRT*.\nWe will begin the talk with a revi ew on the field of motion planning and the principles of RRT based methods \, followed by definitions for a Dubins car-like vehicle\, which represent s a crude description of the dynamics of an aerial vehicle. The main part of the talk will focus on motion planning with time varying constraints an d objectives by using the new RRT variant. The ability of the algorithm\, in generating near-optimal solutions for time varying constraints and obje ctives\, will be presented. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-531@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150202T163000 DTEND;TZID=Asia/Jerusalem:20150202T173000 DTSTAMP:20230603T193429Z URL:https://aerospace.technion.ac.il/events/rock-and-roll-how-flies-contro l-their-flight/ SUMMARY:Rock and Roll – How flies control their flight DESCRIPTION:Lecturer:Dr. Tsevi Beatus\n Faculty:The Physics Department\,\n Institute:Cornell University\, USA\n Location:Classroom 165\, ground floor \, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Flying ins ects can perform a wide array of extreme aerial maneuvers with exquisite a ccuracy and robustness\, outmaneuvering any man-made flying device. As a p hysical system\, a flapping insect is strongly nonlinear with fast-growing mechanical instabilities that must be controlled to allow flight. Hence\, similar to balancing a stick on one's fingertip\, flapping flight is a de licate balancing act made possible only by ever-present\, fast corrective actions. Understanding the underlying mechanisms of insect flight is a maj or challenge\, since this graceful behavior is highly coupled to complex f luid flows and arises from the concerted operation of physiological functi ons across multiple length and time scales. As such\, Insect flight resear ch involves basic concepts from nonlinear dynamics\, fluid mechanics\, neu robiology and control theory\, and has direct application to the developme nt of small flapping robots.\nHere we show how flies control their rotatio nal degrees of freedom: yaw\, pitch and roll. We focus on their body roll angle\, which is unstable and most sensitive degree of freedom. We glue a magnet to each fly and apply a short magnetic pulse that rolls it in mid-a ir. Fast video shows that flies fully correct for perturbations of up to 1 00o within 30±7ms. The roll correction maneuver consists of a stroke-ampl itude asymmetry that is well described by a linear PI controller. For more aggressive perturbations\, we show evidence for nonlinear and hierarchica l control mechanisms. Flies respond to roll perturbations within a single wing-beat\, or 5ms\, making this correction reflex one of the fastest in t he animal kingdom. See image  here. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-525@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150211T163000 DTEND;TZID=Asia/Jerusalem:20150211T173000 DTSTAMP:20230603T193223Z URL:https://aerospace.technion.ac.il/events/film-cooling-of-a-blunt-body-i n-supersonic-high-enthalpy-flows/ SUMMARY:Film Cooling of a Blunt Body in Supersonic High Enthalpy Flows DESCRIPTION:Lecturer:Segoula Uzan\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n During atmospheric re-entry at hypersonic speed or at very high speed flight in the atmosphere\, vehicles experience extremely high thermal loads for relatively long times: the classical thermal protection materials do not survive and need to be replaced by lightweight actively c ooled components. This work investigates experimentally film cooling of a blunt body in a supersonic high enthalpy flow. The coolant\, injected in t he stagnation zone of the blunt body surface against the free stream\, ope rates as a thin\, cool\, insulating layer\, yielding a thickening of the b oundary layer\, thus reducing the temperature gradient of the surface. The experiments were performed in the Aerothermodynamics Laboratory in the Te chnion\, where a plasma arc tunnel enables simulation of high enthalpy flo ws. Two models (with and without injection) were exposed to a Mach 2.2 fre estream with a total enthalpy of 1.7 MJ/kg. Nitrogen and helium were used as coolant gases. A parametric study shows the influence of coolant physic al properties and mass flow rate on the characteristics of the flow surrou nding the model and on the resulting temperature reduction at different lo cations on the test model. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-59@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150219T093000 DTEND;TZID=Asia/Jerusalem:20150219T093000 DTSTAMP:20221031T072634Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%a4%d 7%aa%d7%95%d7%97-2015/ SUMMARY:יום פתוח 2015 DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחללסססס\n Institute:\n Location:הפקולטה להנד סת אוירונוטיקה וחלל\n Zoom: \n Abstract: \n Details: \n בואו לבקר אותנו ביום הפתוח בטכניון\, בדוכ ן שלנו בבית הסטודנט\, ובשלושה סיורים בפקו לטה.\nלפרטים ראו כאן. CATEGORIES:אירועים LOCATION:הפקולטה להנדסת אוירונוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-23@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150219T093000 DTEND;TZID=Asia/Jerusalem:20150219T223000 DTSTAMP:20221030T083405Z URL:https://aerospace.technion.ac.il/events/open-day-2015/ SUMMARY:Open Day 2015 DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Department of Aerospace Engineering\n Zoom: \n Abstract: \n Details: Come visit us at th e Technion's Open Day\, in our stand at the Students Hall\, and in three v isits to the department throughout the day.\nFor details see here.\n CATEGORIES:Events LOCATION:Department of Aerospace Engineering END:VEVENT BEGIN:VEVENT UID:0-17@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem;VALUE=DATE:20150225 DTEND;TZID=Asia/Jerusalem;VALUE=DATE:20150227 DTSTAMP:20221030T083406Z URL:https://aerospace.technion.ac.il/events/55th-israel-annual-conference- on-aerospace-sciences/ SUMMARY:The 55th Israel Annual Conference on Aerospace Sciences DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Tel Aviv/Haifa \n Zoom: \n Abstract: \n Details: The Israel Annual Conference on Aerospac e Sciences\, spanning several generations\, is an important annual event o n the calendar of the aerospace community in Israel. Taking part in this y early event are engineers\, scientists and experts in the field of aeronau tics and astronautics\, representing well-known local aerospace agencies a nd industries\, as well as participants from major research centers worldw ide. The conference hosts a unique undergraduate student competition on ae rospace research and design.\n CATEGORIES:Events LOCATION:Tel Aviv/Haifa END:VEVENT BEGIN:VEVENT UID:0-533@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150309T163000 DTEND;TZID=Asia/Jerusalem:20150309T173000 DTSTAMP:20230603T193503Z URL:https://aerospace.technion.ac.il/events/missile-guidance-and-control/ SUMMARY:Missile Guidance and Control DESCRIPTION:Lecturer:Paul Zarchan\n Faculty:\n Institute:\n Location:Classr oom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The purpose of the one hour talk is to show why I believe the missile guidance and control field is both exciting and challenging. Examp les of the application of mathematics\, physics and computer simulation to the missile problem will be presented. I will include in the presentation both historical perspective and some personal experiences. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-539@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150311T163000 DTEND;TZID=Asia/Jerusalem:20150311T173000 DTSTAMP:20230603T193651Z URL:https://aerospace.technion.ac.il/events/probabilistic-analysis-for-int erface-fracture-and-delamination-failure-of-composites/ SUMMARY:Statistical Analysis for Interface Fracture and Delamination Failur e of Composites DESCRIPTION:Lecturer:Prof. Leslie Banks-Sills\n Faculty:The Dreszer Fractur e Mechanics Lab\, School of Mechanical Eng.\, Tel Aviv University\n Instit ute:\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n A methodology for measuring the interfac e fracture toughness of a crack between two isotropic\, homogeneous materi als and a delamination between two laminae of unidirectional composite mat erials of differing directions is presented. Four cases are considered. Tw o isotropic material pairs are described: glass/epoxy and two ceramic clay s. Similar studies are presented for two cross-ply laminates: 0°/90° an d +45°/-45°.\nThe Brazilian disk specimen was used to carry out mixed mo de fracture tests. The load and crack or delamination length at fracture w ere measured and used in a finite element analysis to determine the displa cement field. An interaction energy or M-integral was used to determine th e stress intensity factors at failure. These in turn were employed to obta in the critical interface energy release rate Gic and one phase angles ψ in two dimensions or two phase angles ψ and ϕ in three dimensions which measure the mode mixity. For the M-integral and for each interface crack o r delamination\, the first term of the asymptotic solution of the field qu antities is required. For two isotropic materials\, these solutions are we ll known. For the laminates described here\, they were determined by the S troh and Lekhnitskii formalisms. A failure criterion determined from first principles is presented. The values of Gic and ψ in two dimensions or ψ and ϕ in three dimensions are used to specify the criterion for each mat erial pair. A statistical analysis is presented. Two approaches are taken: one uses the t-statistic to predict a 10% probability of failure\; the se cond uses a standard normal variate to predict a 10% failure probability w ith 95% confidence. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-536@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150325T163000 DTEND;TZID=Asia/Jerusalem:20150325T173000 DTSTAMP:20230603T193555Z URL:https://aerospace.technion.ac.il/events/the-aero-optic-phenomenon-in-a -compressible-shear-layer/ SUMMARY:The Aero-Optic Phenomenon in a Compressible Shear Layer DESCRIPTION:Lecturer:Yasmin Ribak\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The aero-optic effect is a major topic of interest due to its relevance in various applications\, which involve interactions between propagated laser beams and an inhomogeneous medium (such as the variable- density flow fields\, which form within compressible boundary and free she ar layers). By creating aero-optical aberrations\, this phenomena results in significant reduction of optical system performance and yield lower pea k energy of the light intensity and wider energy distribution around the c entral spot of the beam. The broad range of industrial applications\, wher e such an effect is observed\, includes missiles with optical seekers\, ai rborne telescopes\, airborne free-space communication systems\, and high- powered lasers on combat air vehicles.\nIn the present research\, quantita tive and qualitative methods are devised in order to characterize the aero -optic effect in the mixing layers of a compressible free jet. Towards vis ualization of the mixing layer between the ambient and the free jet\, two optical measurement techniques (Shadowgraph and Schlieren) are used in a q ualitative manner. The intensity of the laser\, along with its distributio n\, is evaluated and the deviations of the initially collimated beam are a nalysed. Enhanced understanding of the laser beam distortions associated w ith a compressible jet contributes to the pool of efforts towards developi ng an optimal technique which can form an undistorted wave front. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-537@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150330T163000 DTEND;TZID=Asia/Jerusalem:20150330T173000 DTSTAMP:20230603T193614Z URL:https://aerospace.technion.ac.il/events/engineering-technological-and- system-aspects-in-the-development-of-the-trophy-system/ SUMMARY:Engineering\, Technological and System Aspects in the Development o f the Trophy System DESCRIPTION:Lecturer:Dr. Gil Yudilevitch\n Faculty:Senior System Engineer\, Rafael\n Institute:\n Location:Classroom 165\, ground floor\, Library\, A erospace Eng.\n Zoom: \n Abstract: \n Details: \n Trophy is an Active Prot ection System for ground vehicles (APS).\nFirst we’ll define what active protection is and what APS is. Then\, we’ll present the main system cha llenges that we had during the development process and the solution that w ere implemented.\nWe’ll present and discuss the very challenging timelin e of the neutralization scenario\, which is the main cause for the selecti on of the Trophy system concept. In addition\, we’ll present 3 more syst em challenges and their solutions: Safety\, Performance Verification and F ielding. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-530@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150401T163000 DTEND;TZID=Asia/Jerusalem:20150401T173000 DTSTAMP:20230603T193408Z URL:https://aerospace.technion.ac.il/events/sea-lion-swimming-and-ship-air -wake-research-two-projects-at-the-george-washington-university/ SUMMARY:Sea Lion Swimming and Ship Air Wake Research\, Two Projects at the George Washington University DESCRIPTION:Lecturer:Dr. Ken Friedman\n Faculty:Department of Mechanical an d Aerospace Eng.\,\n Institute:School of Eng. and Applied Sciences\, Georg e Washington University\, Washington\, DC\n Location:Classroom 165\, groun d floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Sea Lion Swimming:\nThe main objective of this research is to explore a mecha nism for underwater propulsion that leaves little traceable wake structur e while producing high levels of thrust. A potential  biological model i s the California sea lion\, an aquatic mammal that produces thrust primari ly using its foreflippers\, unlike most marine swimmers which use caudal fin oscillation. Sea lions use a “clap and glide” method which appear s to have no characteristic frequency and thus are expected to generate a significantly different wake. In an effort to build a robotic sea lion fl ipper for water tunnel experimentation\, flipper kinematics have been qua ntified for the first time in both two and three dimensions\, and the fli pper’s geometry has been extracted using three non-invasive methods whi ch will be briefly compared for their overall quality and level of detail captured.\nShip Air Wake:\nShipboard launch and recovery of naval rotary w ing aircraft is vital to several of the Navy’s mission areas\, but is c onsidered challenging and potentially dangerous\, often limited by rapidly  changing flow conditions due to ship motion\, air turbulence created by the ship’s superstructure\, and the dynamic interaction between the ves sel’s air wake and the rotor wake. This talk will present comparison be tween detailed in situ air wake measurements on a 32.9 m (108 ft) long Na vy vessel\, and both wind tunnel and CFD results (with matching Reynolds n umbers)\, in an attempt to validate computations for reducing the require d flight testing. Preliminary results from in situ dynamic interface expe riments will also be presented\, with a scaled RC helicopter producing an equivalent rotorcraft wake while mounted on a pole at a representative he ight. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-44@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150402T110000 DTEND;TZID=Asia/Jerusalem:20150402T150000 DTSTAMP:20221030T083407Z URL:https://aerospace.technion.ac.il/events/open-day-for-graduate-studies/ SUMMARY:Open Day for Graduate Studies DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Entrance to th e Department of Aerospace Engineering Building\n Zoom: \n Abstract: \n Det ails: On April 2nd\, the Department of Aerospace Engineering will hold an “open day” for graduate studies (M.Sc. and Ph.D.). Undergraduate and g raduate students from the Technion and other universities are also invited to attend. Graduate students from the Department of Aerospace Engineering will be available as “guides\,” and faculty members will also take pa rt in the day.\nFor full details\, see here.\n CATEGORIES:Events LOCATION:Entrance to the Department of Aerospace Engineering Building END:VEVENT BEGIN:VEVENT UID:0-534@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150413T163000 DTEND;TZID=Asia/Jerusalem:20150413T173000 DTSTAMP:20230603T193520Z URL:https://aerospace.technion.ac.il/events/modelling-and-control-of-aeroa coustic-noise/ SUMMARY:Modelling and Control of Aeroacoustic Noise DESCRIPTION:Lecturer:Dr. Oksana Stalnov\n Faculty:University of Southampton \, UK\n Institute:\n Location:Classroom 165\, ground floor\, Library\, Aer ospace Eng.\n Zoom: \n Abstract: \n Details: \n The reduction of aeroacous tic noise is a major engineering challenge that affects a wide range of in dustries from air transport to wind energy. For instance\, noise pollution for communities near airports is a major constraint on further growth of air transport traffic. In particular\, when landing gears are being deploy ed during the approach phase of flight they become the main contributor to the airframe noise. Similarly\, the noise emitted from wind-turbine blade s is limiting further spread of onshore wind-farm due to public concern ab out noise pollution. The noise emitted from the blades is predominately ae rodynamic and is generated when a turbulent boundary layer interacts with a trailing-edge of a blade. Reducing the noise level while maintaining aer odynamic performance is a challenge today and it is likely to be more impo rtant in the future.\nThis talk will focus on enhancing\, predicting and c ontrolling aeroacoustic performance. The first part of the talk will discu ss the noise generation associated with bluff bodies\, such as circular\, and the application of flow control for noise reduction. Experiments were performed in the University of Southampton’s open jet anechoic facility and closed-loop aerodynamic wind-tunnel to investigate the effect of blowi ng circumferential angle and strength and found that noise can be reduced when flow-control is applies under optimal conditions. The second part of the talk will discuss further development of airfoil self-noise prediction model. This work extends previously published TNO-Blake semi-infinite bro adband airfoil self-noise model to incorporate finite chord noise radiatio n Amiet model with recent improvements in modelling of boundary-layer para meters. These results demonstrate that aerodynamic noise of NACA-0012 airf oil section can be predicted with less than 2dB while avoiding parameter t uning. Furthermore\, the TNO-Amiet model captures the measured oscillation in both far-field spectra and directivity patterns. The results of these studies could be applied in the future to guide industry to improve both a erodynamic and aeroacoustic performance. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-529@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150415T163000 DTEND;TZID=Asia/Jerusalem:20150415T173000 DTSTAMP:20230603T193351Z URL:https://aerospace.technion.ac.il/events/effect-of-trailing-edge-elasti city-on-the-acoustic-signature-of-an-airfoil-in-unsteady-flow/ SUMMARY:Effect of Trailing Edge Elasticity on the Acoustic Signature of an Airfoil in Unsteady Flow DESCRIPTION:Lecturer:Vladimir Katz\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Trailing edge noise is identified as a major component of airframe noise\, particularly during airplanes approach for landing\, whe n extensive use is made of high-lift devices. Consequently\, significant e fforts have been made to analyze the acoustic signature of such devices\, in various setups and flight conditions. Common to almost all of these wor ks is a consideration of a rigid lift device\, in which the impacts of ele ment geometry and orientation are examined.\nThe objective of the present work is to apply existing vibroacoustic methodologies to examine the effec t of trailing edge elasticity on the acoustic radiation of an otherwise ri gid airfoil. We consider the far-field radiation of a thin airfoil attache d to a flexible downstream appendage\, and compare it with radiation by a counterpart rigid structure. Flow unsteadiness is modeled as an incident l ine vortex\, convected by the mean flow in the vicinity of the airfoil.\nA ssuming low-Mach high-Reynolds flight conditions\, the near-field flow is examined based on thin-airfoil theory\, and the far-field sound is compute d using a compact-body acoustic analogy. Results describe the impact of tr ailing edge elasticity on near- and far-field flow characteristics\, and i ndicate on the amplifying  effect of edge flexibility on the far-field so und. In particular\, far-field radiation in the non-rigid case is affected by stronger edge-point interactions with incoming vorticity\, as well as by long-time flow-induced oscillations at the system least stable eigenfre quency. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-522@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150429T163000 DTEND;TZID=Asia/Jerusalem:20150429T173000 DTSTAMP:20230603T193130Z URL:https://aerospace.technion.ac.il/events/prediction-of-the-nonlinear-in teraction-between-a-2d-instability-wave-and-the-mean-flow-of-unbounded-she ar-flows/ SUMMARY:Prediction of the nonlinear interaction between a 2D instability wa ve and the mean flow of unbounded shear flows DESCRIPTION:Lecturer:Ilia Malkine\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In recent years\, active flow control (AFC) has become a n ew branch in fluid mechanics. The long term goal of the current research i s to predict and understand the change in incompressible flow field over a separated wing due to the addition of a two-dimensional (2D) instability wave.\nIn the present work the nonlinear interaction between the mean flow and a 2D coherent disturbance in a 2D turbulent wake is investigated.  F or this purpose a theoretical model is examined. The proposed model is bas ed on the triple decomposition method: it is assumed that the flow field c onsists of a quasiparallel mean flow\, coherent sinusoidal perturbation an d incoherent turbulent fluctuation which are taken into account using a co nstant eddy viscosity model.\nDifferent normalizations of the linear solut ion are examined. In addition\, the effects of Reynolds number\, frequency and amplitude of the forced wave on the evolution of the flow field are i nvestigated. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-526@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150510T163000 DTEND;TZID=Asia/Jerusalem:20150510T173000 DTSTAMP:20230603T193254Z URL:https://aerospace.technion.ac.il/events/a-new-concept-reaching-the-bes t-achievable-control-by-decomposing-the-sensitivity-function/ SUMMARY:A New Concept Reaching the Best Achievable Control by Decomposing t he Sensitivity Function - Part 1 DESCRIPTION:Lecturer:Prof. L. Keviczky\n Faculty:Department of Automation a nd Applied Informatics\, Budapest University of Technology\, and Economics (BUTE) and Computer and Automation Research Institute (CARI) of the Hunga rian Academy of Sciences (HAS)\n Institute:\n Location:Classroom 165\, gro und floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n I n optimization theories the difference (distance) between the optimal and actual case is called loss. These set of talks introduces a new theory whi ch provides a new platform for control system optimization. This concept i s based on a special decomposition of the sensitivity function of a closed -loop\, defined as S=1/(1+CP)\, which makes possible to reformulate the cl assical paradigm: which is the best achievable control? Here C is the cont roller and P is the process.\nThe three decomposed parts are the design lo ss\, the realizability loss and the modeling loss.\nIn the theoretical opt imal case the sensitivity function is zero\, which can never be reached. T he decomposition helps to formulate the optimization of the contributing l osses independently. The special new decomposition gives a possibility to optimize the three parts separately\, but unfortunately not independently\ , because these components are not orthogonal. Therefore\, always some ite rative solution can be applied and the properties of the three parts must be investigated separately. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-523@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150511T163000 DTEND;TZID=Asia/Jerusalem:20150511T173000 DTSTAMP:20230603T193147Z URL:https://aerospace.technion.ac.il/events/a-new-concept-reaching-the-bes t-achievable-control-by-decomposing-the-sensitivity-function-part-2/ SUMMARY:A New Concept Reaching the Best Achievable Control by Decomposing t he Sensitivity Function - Part 2 DESCRIPTION:Lecturer:Prof. L. Keviczky\n Faculty:\n Institute:Department of Automation and Applied Informatics\, Budapest University of Technology\, and Economics (BUTE) and Computer and Automation Research Institute (CARI) of the Hungarian Academy of Sciences (HAS)\n Location:Classroom 165\, gro und floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n O ptimization of the design loss\nThe optimization of the design loss result s in selecting the fastest reference models under the amplitude constraint s of the actuators. It is possible to develop an iterative redesign techni que for the selection of best reachable reference model. It is very rare t hen we have an analytical solution for this optimization\, instead repeate d simulation runs results in the best reference model. The optimization pr ocess is presented by several simulation examples.\nOptimization of the re alizability loss\nFor the optimization of the realizability loss new (ener gy and supremum) norms E2 and E͚ are applied instead of the classical nor ms H2 and H͚. Unfortunately these last norms are not applicable for such – mostly integrating – regulator classes\, which are important for ind ustrial applications. The norms E2 and E͚ are certain generalizations of the classical norms H2 and H͚. The optimization of E2 can be usually solv ed by the application of certain Diophantine equations. The optimization o f E͚ can be usually solved by the iterative solution of a nonlinear equat ion system. Several simple examples are shown to ease the understanding of the high level mathematical procedures.\nOptimization of the modeling los s\nThe modeling loss considers the process identification in two parallel closed loops\, where one is the original and the other is based on the ava ilable model. The optimization of the modeling loss results in a special b inary form of the reference signal\, where the switching condition can be computed via a specially formed filter. It is interesting that the optimal reference signal excitation concentrates the frequency weights around the cutting frequency. Simple but convincing simulation runs are presented to prove the much higher efficiency of the optimal identification comparing to other excitation signals. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-521@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150513T163000 DTEND;TZID=Asia/Jerusalem:20150513T173000 DTSTAMP:20230603T193107Z URL:https://aerospace.technion.ac.il/events/a-new-concept-reaching-the-bes t-achievable-control-by-decomposing-the-sensitivity-function-part-3/ SUMMARY:A New Concept Reaching the Best Achievable Control by Decomposing t he Sensitivity Function - Part 3 - Summary DESCRIPTION:Lecturer:Prof. L. Keviczky\n Faculty:\n Institute:Department of Automation and Applied Informatics\, Budapest University of Technology\, and Economics (BUTE) and Computer and Automation Research Institute (CARI) of the Hungarian Academy of Sciences (HAS)\n Location:Classroom 165\, gro und floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n I n the previous lectures an interesting new approach based on the special d ecomposition of the sensitivity function was introduced and discussed. Thi s method optimizes the three major components (design loss\, realizability loss and modeling loss) separately.\n\n“Nothing is more practical than a good theory.” - Boltzmann\n\nThis summary lecture presents simple exam ples to show the efficiency of the method and ease the understanding.\n\n “The examples are more useful than formulas.” - Newton\n\nFirst the op timization of the design loss is shown by two examples\, where an iterativ e redesign technique is used to find the best reachable reference model\, i.e.\, the fastest control system can be ever reached under practical cons traints. It is very rare then we have an analytic solution for this optimi zation\, instead repeated simulation runs results in the best reference mo del.\nThen the optimization of the realizability loss is presented\, which is a pure mathematical problem as the examples will show. For the E2 (and H2) norms the solution is to solve a Diophantine equation which can be do ne by solving special linear system equations. For the E͚ (and H͚) norms the problem can be solved via the Navelinna-Pick approximation procedure\ , which results in a nonlinear system equation.\nFinally the optimization of the modeling loss is treated. It will be shown in the examples that the best modeling loss can be obtained if the closed-loop control system is e xcited by a binary reference signal\, where the switching condition provid es the optimality. The example will show clearly that such optimal excitat ion concentrates the frequency content of the signal around the cutting fr equency\, this is the frequency domain where we must have the most accurat e models. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-524@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150527T163000 DTEND;TZID=Asia/Jerusalem:20150527T173000 DTSTAMP:20230603T193205Z URL:https://aerospace.technion.ac.il/events/investigation-of-h2o-vitiated- combustion-in-a-low-equivalence-turbo-jet-combustor/ SUMMARY:Investigation of H2O-Vitiated Combustion in a Low-Equivalence Turbo -Jet Combustor DESCRIPTION:Lecturer:Akiva M.G. Sharma\n Faculty:Department of Aerospace En gineering\n Institute:Technion – Israel Institute of Technology\n Locati on:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abst ract: \n Details: \n Today\, more than ever before\, the necessity of prod ucing low emissions gas turbines is of paramount importance. Reducing the emission of Nitrogen Oxides in particular has been of primary focus. In th is vein\, there has been a continuing trend towards a higher degree of fue l-air premixing prior to combustion for the sake of reducing NOx emission. The various methods that have been developed for this purpose are not wit hout their flaws however. Some may decrease NOx while increasing CO and UH C emissions. Some may decrease NOx while sacrificing thermal efficiency. A s such there is still a search for a technology that can combine the stren gths of all the methods without any of their weaknesses.  Flameless oxida tion is a technology that has been developed during the last two decades a nd shows promise for being an alternative method of achieving low NOx emis sions. Thus far\, it has been successfully applied to industrial furnaces. The patented combustion principle of flameless oxidation (FLOX®)\, devel oped by WS Wärmeprozesstechnik is based on high internal flue gas recircu lation which leads to a dilution of the combustion zone. The high recircul ation ratios are achieved by the momentum of the air and fuel jets enterin g the combustion chamber.\nThe work contained herein is twofold\; in the f irst part atmospheric experiments are conducted on a cylindrical\, lean\, non-premixed combustor. Various combustor design parameters such as fuel-a ir injection configuration\, oxidizer pre-heating\, and steam injection ar e investigated with respect to flame temperature\, volume and emission for mation. Based on this work\, a novel combustor design is developed\, which is capable of burning methane as a stand-alone combustor\, or part of a s equential system that contains water as an inlet constituent.\nIn the seco nd part of the work\, the combustion chamber is modeled as a chemical reac tor network in order to select a reduced chemical mechanism for numerical calculations. The physical chamber was meshed and CFD simulations were per formed under matching boundary conditions to that which experimental measu rements were taken using the selected reduced mechanism.  CFD results for a basic case are validated using the experimental results and show excell ent agreement with the NOx\, and temperature measurements. The CFD is used to gain further insight into the effect of water injection on methane com bustion. It is shown that steam effectively reduces the NOx production by dilution of the flame as well as by a chemical route wherein the concentra tion of the OH radical pool changes and affects the chemistry of the NOx f ormation.  It has been demonstrated that while pre-heating does indeed en hance mixing inside the chamber and thus promotes flameless combustion\, i t also increases NOx production and at sufficient levels of H2O dilution\, preheating is unnecessary.  A combination of preheating and H2O vitiate allows for predictions of ultra-low pollutant levels and smooth temperatur e profiles at lower recirculation values prescribed by other authors. A no vel combustor design and injector configuration has been designed that pre dicts characteristic emissions and properties of flameless combustion. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-507@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150608T163000 DTEND;TZID=Asia/Jerusalem:20150608T173000 DTSTAMP:20230603T192508Z URL:https://aerospace.technion.ac.il/events/a-hybrid-computational-method- for-dynamic-thermal-analysis-of-structures-including-thin-layers/ SUMMARY:A Hybrid Computational Method for Dynamic Thermal Analysis of Struc tures Including Thin Layers DESCRIPTION:Lecturer:Israel Tuval\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Thin layers appear in many applications in the field of ae rospace engineering. Examples include external thin coatings of bare panel s exposed to periodic solar radiation\, or the internal thin glue layer co nnecting the complex parts in aircraft or satellites\, which are exposed t o a sudden thermal shock.\nThe thin layer has different mechanical and the rmal properties from its surroundings and is usually smaller by an order o f magnitude from its surrounding media.\nThe two opposite approaches to ha ndle the modeling and analysis of such thin layers are either to ignore th e layer or to fully model it\, using the Finite Element (FE) method for ex ample. The former approach may suffer from severe inaccuracy\, while the l atter is time consuming for the human modeler and computationally expensiv e.\nSpecial asymptotic models that constitute a compromise between these t wo approaches have been proposed for linear heat transfer and linear elast icity. In these models the thin layer is replaced by an interface of zero thickness\, and specific jump conditions are imposed in order to represent the special effect of the layer.\nIn our work we adopt the first-order as ymptotic interface model that was developed by Bövik and Benveniste and i ncorporate it in a FE formulation for linear time-dependent heat conductio n problems. In this seminar we will show the capability of this approach t o yield an accurate and efficient computational scheme for both internal a nd external thin layers. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-41@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150610T123000 DTEND;TZID=Asia/Jerusalem:20150610T143000 DTSTAMP:20221030T083409Z URL:https://aerospace.technion.ac.il/events/faculty-picnic/ SUMMARY:Faculty Picnic DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty front yard\n Zoom: \n Abstract: \n Details: A faculty picnic for students and fa culty members.\n CATEGORIES:Events LOCATION:Faculty front yard END:VEVENT BEGIN:VEVENT UID:0-517@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150610T163000 DTEND;TZID=Asia/Jerusalem:20150610T173000 DTSTAMP:20230603T192803Z URL:https://aerospace.technion.ac.il/events/the-effect-of-energetic-ingred ients-on-the-burning-rate-of-solid-propellants/ SUMMARY:The Effect of Energetic Ingredients on the Burning Rate of Solid Pr opellants DESCRIPTION:Lecturer:Hagit Greenfeld\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n The burning rate of a solid propellant is a fundamental characteristic\, which is measured for every propellant composition that is aimed to be used in a rocket motor. The burning rate measuring procedur e in the lab requires mixing of all propellant ingredients\, casting of th e material into moulds\, hot curing of the material\, extracting strand sa mples and burning of many samples at various pressures. This procedure is long and requires significant resources\, thus the motivation for developi ng a theoretical model\, able to predict the burning rate of a given compo sition is obvious.\n A solid propellant is a mixture of a polymeric binde r that contains a hydrocarbon fuel\, plasticizer\, surface agents\, cross linking agents etc. together with crystalline oxidizer particles in two or three size groups. The combustion of such a mixture is very complex and i s affected by several combustion mechanisms and by different type of flame s.  The combustion mechanism depends on the pressure\, the amount of oxid izer particles and their size distribution. The heat transfer from the fla me plane to the propellant surface determines the propellant burning rate. \nThe well-known\, BDP model\, developed by three investigators\, Beckstea d\, Derr and Price\, is an analytical model that presents a set of equatio ns with a closed solution that provides the burning rate of a given compos ition as a function on pressure.\nIn the frame of the present work\, the B DP model was implemented in a computer code developed in Rafael. A compari son of the prediction to experimental data reported in literature and self preformed experimental data was conducted. In the second stage\, a model correction was proposed in order to improve the prediction for low burning rate propellants.\nIn the experimental part of the research 14 "reduced s moke" propellant compositions were tested and about 100 experiments were c onducted at various pressures. The revised model that was developed in the present study shows a very good agreement with the tested propellants. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-508@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150617T163000 DTEND;TZID=Asia/Jerusalem:20150617T173000 DTSTAMP:20230603T192527Z URL:https://aerospace.technion.ac.il/events/experimental-investigation-of- projectile-resisting-force-in-polycarbonate-targets/ SUMMARY:Experimental Investigation of Projectile Resisting Force in Polycar bonate Targets DESCRIPTION:Lecturer:Alon Weiss\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n The earliest recorded studies on terminal ballistics date ba ck to eighteenth century ideas by Euler and Robins who argued that project ile resisting force remains constant during the penetration process. Later work by Poncelet (1829)\, Resal (1895) and Petry (1910) has paved the way to modern penetration science and engineering in deriving velocity depend ent formulae for resisting force.\nThis work presents a comprehensive expe rimental and analytical observation on polycarbonate ballistic response. D eep penetration and plate perforation tests were conducted with several th icknesses of polycarbonate targets at normal impact and within a striking velocity range of 500-900 m/sec. Projectile penetration location\, velocit y and acceleration\, were monitored using high-speed cameras for tracking the depth of penetration path and orientation.\nOne of the primary objecti ves of this work was to examine the possibility of a simple constitutive e quation to predict the depth of penetration for rigid projectiles into pol ycarbonate targets. Experimental results have confirmed the original hypot hesis of Euler that the resisting force during penetration is nearly const ant. This observation is based on a wide range of test data with ogive hea d armor piercing projectiles.\nFollowing the standard approach of steady s tate cavity expansion\, cavitation fields in spherical and cylindrical con figurations are derived and applied to predict the specific cavitation ene rgy for polycarbonate targets. The specific cavitation energy\, identified with the cavitation pressure\, can be used for estimating the penetration depth and the ballistic limit of protective plates in which ductile hole- formation is the dominant mode of failure.\nIt is suggested that not all o f the projectile kinetic energy converts to plastic deformation energy\, p art of the projectile energy is diverted to the cracking process within th e layer adjacent to the projectile. We obtain formulae for the cavitation pressure that apply for assessment of resisting stress during projectile b allistic penetration. We found that the spherical cavitation pressure in p resence of damaged zones is in satisfactory agreement with test data. Mate rial response is modeled as elastic/perfectly-plastic of Mises type with n eglect of elastic compressibility. Sensitivity to failure strain is examin ed and useful closed form formulae are derived. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-516@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150624T163000 DTEND;TZID=Asia/Jerusalem:20150624T173000 DTSTAMP:20230603T192746Z URL:https://aerospace.technion.ac.il/events/tracking-in-the-presence-of-fi eld-of-view-constraints-using-probabilistic-data-association-2/ SUMMARY:Tracking in the Presence of Field-of-View Constraints Using Probabi listic Data Association DESCRIPTION:Lecturer:Matan Yeger\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Modern tracking systems are required to estimate the distri bution of targets in a surveyed scene while coping with a variety of uncer tainties\, such as unknown number of targets\, unknown target motion model s\, missed detections and clutter (false measurements). An even more chall enging tracking scenario may occur when trying to track targets in a scene with Field-of-View (FOV) constraints. Such situations may arise in urban environments including man-made occlusions (e.g.\, buildings)\, or in envi ronments involving topographic constraints (e.g.\, mountains). In such sit uations the tracking system needs to reason about information not readily accessible\, when the target resides in unobserved regions of the environm ent.\n We address the problem of tracking a single\, non-maneuvering targ et\, moving through a scene containing unobserved regions that are a prior i known to the tracker. A modified Probabilistic Data Association (PDA) fi lter is developed\, that can take into account unobserved regions\, in add ition to target originated measurements\, missed detections\, and clutter. The modification is based on a "negative" information concept\, whereby e xpected but actually missing measurements in a scene containing unobserved regions may be regarded as useful information that can be exploited by th e tracking system. In order to use this kind of information it is formulat ed as a fictitious measurement that embodies the essence of the "negative" information. The fictitious measurement\, and its associated measurement noise covariance\, are formulated based on the hidden region’s geometry. This measurement is used to update the target estimated state and error c ovariance by using a regular Kalman filter approach within the standard PD A framework.\n The performance of the modified PDA filter is studied via numerical simulations. The simulations demonstrate track continuity when t he target resides in occluded regions\, with a controlled growth of the as sociated error covariance\, thus facilitating robust tracking when the tar get becomes detectable again. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-35@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150625T193000 DTEND;TZID=Asia/Jerusalem:20150625T203000 DTSTAMP:20221030T083410Z URL:https://aerospace.technion.ac.il/events/b-sc-graduation-2015/ SUMMARY:B.Sc. Graduation 2015 DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty front yard\n Zoom: \n Abstract: \n Details: On 25.6.15 the department will hold a B.Sc. graduation ceremony.\n CATEGORIES:Events LOCATION:Faculty front yard END:VEVENT BEGIN:VEVENT UID:0-515@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150701T163000 DTEND;TZID=Asia/Jerusalem:20150701T173000 DTSTAMP:20230603T192730Z URL:https://aerospace.technion.ac.il/events/experimental-study-of-unsteady -aerodynamics-during-flapping-flight-of-birds/ SUMMARY:Experimental Study of Unsteady Aerodynamics during Flapping Flight of Birds DESCRIPTION:Lecturer:Roi Gurka\n Faculty:School of Coastal and Marine Syste ms Science\n Institute:Coastal Carolina University\, SC\, USA\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Case Study: Starling\, Sandpiper and Robin\nBirds’ uniq ue characteristics such as wing shape\, flexibility\, feathers\, and flapp ing motion\, result in high aerodynamic performance. Flapping flight mode is common in low Reynolds number flyers and the contribution of unsteady e ffects to lift and drag is not entirely understood. To gain insight about the unsteady contribution\, a controlled study in an avian wind tunnel on the near wake flow behind freely flying birds was performed. Long duration \, time resolved particle image velocimetry (PIV)\, combined with high spe ed imaging has been used to characterize the various flow features at the bird’s wake that are associated with flapping flight. Time series of the velocity and the vorticity fields have been expressed as composite wake p lots\, which reveal various characteristics of the wake during the upstrok e (US) and downstroke (DS) phases of the flapping mode as well as the tran sition between US to DS and vice versa. Unsteady drag and lift components have been estimated over these wingbeat cycles\, demonstrating how the bir d manifests its aerodynamic performance through the kinematics of the wing s. Comparison between the near wake fields of the three birds shows remark able similarity in their wake structure. We have identified the presence o f what appears to be an overlap of two distinct patterns during the transi tion from US to DS. Over these regions\, the majority of net positive circ ulation is accumulated\, which indicates that this overlap may be a key fe ature in producing lift\, and thus contribute to the observed high aerodyn amic performance. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-509@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150708T163000 DTEND;TZID=Asia/Jerusalem:20150708T173000 DTSTAMP:20230603T192545Z URL:https://aerospace.technion.ac.il/events/the-2015-merhav-prize-seminar- state-estimation-in-systems-with-random-coefficients/ SUMMARY:The 2015 Merhav Prize seminar - State Estimation in Systems with Ra ndom Coefficients DESCRIPTION:Lecturer:Daniel Sigalov\n Faculty:\n Institute:Technion – Isr ael Institute of Technology\n Location:Classroom 165\, ground floor\, Libr ary\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n State estimation in dynamical systems with randomly switching coefficients is an important  problem with a variety of applications. The most commonly met problems t hat are formulated within the random coefficients state-space approach\, are maneuvering target tracking and fault-tolerant filtering. A related cl ass of problems is referred to as data association or data ambiguity. In this family\, the estimation process is further complicated by the fact th at the acquired data has uncertain origin. Typical applications include t arget tracking in clutter and multiple target tracking.  In this talk we aim at deriving a unified framework for state estimation problems under data and model uncertainties. First\, we present the problem of tracking a maneuvering target restricted to perform a bounded number of maneuvers a nd show that\, despite the inherent deviation from the standard Markov sw itching assumption underlying most state-of-the-art algorithms\, it may b e reformulated and solved using a generalized version of such tools. We p roceed with an overview of linear minimum mean-square error (LMMSE) algor ithms for state estimation in systems with random coefficients. We show th at the novel formulation allows treatment of problems that have not been addressed in the LMMSE sense in the past. These include target tracking i n clutter and multiple target tracking. Finally\, we present a general fr amework\, accompanied by a variety of applications\, which allows a utiliz ation of a single IMM-like algorithm to solve a variety of state estimatio n problems.  These include maneuvering target tracking\, clutter and data association\, multiple target tracking\, tracking of splitting targets an d more. In some cases it will be shown that the resulting unified IMM-lik e filter reduces to some classical algorithms such as PDA and JPDA. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-518@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150722T163000 DTEND;TZID=Asia/Jerusalem:20150722T173000 DTSTAMP:20230603T192823Z URL:https://aerospace.technion.ac.il/events/limit-cycle-oscillations-of-a- pre-tensed-membrane-strip/ SUMMARY:Limit-Cycle Oscillations of a Pre-tensed Membrane Strip DESCRIPTION:Lecturer:Ariel Drachinsky (Arik)\n Faculty:Department of Aerosp ace Engineering\n Institute:Technion – Israel Institute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \ n Abstract: \n Details: \n The seminar will present a computational and ex perimental study of the nonlinear aeroelastic behavior of a pre-tensed\, h igh aspect-ratio\, thin membrane strip. The goal of the study is to derive and validate a computational model that can be used for analysis and desi gn of membrane strips\, for the purpose of energy harvesting from flutter at low airspeeds.  The mathematical model is based on a pre-tensed-beam m odel\, accounting for bending and torsional stiffening effects due to pret ension and large deformations. The aerodynamic model is a potential flow m odel. The equations of motion are written as a set of nonlinear ordinary d ifferential equations\, using Galerkin’s method\, and are simulated nume rically. The nonlinear aeroelastic model is used to study the oscillation characteristics of the membrane strip in the various stability regions. Th e effects of initial pretension and non-linear stiffening on energy-harves ting potential of the system are studied. The combined effect of the prelo ad on the flutter onset speed\, on the flutter frequency and amplitude\, a nd on the loss of orbital stability\, indicates that an optimal preload ca n be determined based on the intended airspeed range for energy harvesting . A series of wind tunnel tests was conducted\, in which the flutter onset velocity\, and the post-flutter frequencies and amplitudes were measured. Good agreement between the experimental data and computational results va lidate the computational model. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-511@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150729T163000 DTEND;TZID=Asia/Jerusalem:20150729T173000 DTSTAMP:20230603T192617Z URL:https://aerospace.technion.ac.il/events/transition-in-plane-poiseuille -flow/ SUMMARY:Transition in Plane Poiseuille Flow DESCRIPTION:Lecturer:Federico Roizner\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n Transition to turbulence initiated by linear transient growth mechanism in plane Poiseuille flow is demonstrated in the present study. A novel analytical approximation of the linear transient growth mec hanism enables us to perform a secondary linear stability analysis of the modified base-flow. Two possible routes to transition will be presented.  The first one is initiated by four decaying odd normal modes which form a counter-rotating vortex pair\, whereas the second is initiated by five e ven decaying modes which form a pair of counter-rotating pairs. Because of the minimal number of modes participating in the transition process it is possible to follow the transition stages analytically employing  multipl e time scale analysis. The analytical results are compared with the direct numerical simulations demonstrating a very good agreement.  CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-49@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150806T081500 DTEND;TZID=Asia/Jerusalem:20150806T163000 DTSTAMP:20221030T083411Z URL:https://aerospace.technion.ac.il/events/seminar-on-analysis-design-and -manufacturing-of-propellers-and-rotors-from-composite-materials/ SUMMARY:Seminar on "Analysis\, Design and Manufacturing of Propellers and R otors from Composite Materials" DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Facu lty Auditorium\, room no. 235\n Zoom: \n Abstract: \n Details: A seminar o n "Analysis\, Design and Manufacturing of Propellers and Rotors from Compo site Materials" will be held Aug. 06 \,2015\, in Aerospace Faculty.\n \n CATEGORIES:Events LOCATION:Aerospace Faculty Auditorium\, room no. 235 END:VEVENT BEGIN:VEVENT UID:0-512@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150812T163000 DTEND;TZID=Asia/Jerusalem:20150812T173000 DTSTAMP:20230603T192638Z URL:https://aerospace.technion.ac.il/events/recent-advances-in-computation al-fracture-mechanics/ SUMMARY:Recent Advances in Computational Fracture Mechanics DESCRIPTION:Lecturer:Prof. Haim Waisman\n Faculty:Civil Engineering and Eng ineering Mechanics\n Institute:Columbia University\n Location:Classroom 16 5\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Detail s: \n The modelling of cracks and shearbands\, arising from brittle and du ctile response of materials\, poses significant computational challenges. In this talk I will present our recent developments in the field of comput ational fracture mechanics that address some of these challenges.\nThe fir st part of the talk\, devoted to brittle fracture\, will focus on a new fo rmulation based on a high order extended finite element method and Irwin ’s integral to extract Strain Energy Release Rates in linear elastic fra cture mechanics. Extended finite element methods provide an attractive alt ernative to standard finite elements in that they do not require fine spat ial resolution in the vicinity of discontinuities nor do they require repe ated re-meshing to properly address propagation of cracks. The significanc e of the approach presented is that it provides an efficient alternative t o the J-integral method and can circumvent some of the J-integral limitati ons when applied to 3D fracture modelling and crack coalescence.\nThe seco nd part of the talk will focus on dynamic fracture of metals which may be brittle or ductile depending on factors such as material properties\, load ing rate and specimen geometry. At high strain rates\, a thermo-plastic in stability known as shear banding may occur\, which typically precedes frac ture while at lower rates brittle fracture is observed. To date there is n o model that captures both phenomenon in single framework. To this end\, I will present a novel mixed finite element formulations with diffusive reg ularization for shear band instabilities combined with a phase field metho d for fracture. The governing nonlinear PDE system is solved robustly by a n implicit monolithic solver. The main formulations along with some numeri cal examples to illustrate the performance of the model will be presented. I will briefly discuss a range of challenges including discretization and element formulation\, mesh sensitivity\, large deformations and re-meshin g\, parallel computing and solver technology. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-510@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150902T163000 DTEND;TZID=Asia/Jerusalem:20150902T173000 DTSTAMP:20230603T192601Z URL:https://aerospace.technion.ac.il/events/cooperative-estimation-via-alt ruism/ SUMMARY:Cooperative Estimation Via Altruism DESCRIPTION:Lecturer:Nitai Stein\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Cooperative estimation has been an active area of research in recent time. The idea underlying most state-of-the-art methods is to sh are information\, obtained separately by subsystems comprising the system\ , and to use that information in an adequately designed (centralized or di stributed) estimation algorithm that generates a common (global) estimate. The estimation performance that can thus be attained should be superior t o that of each local estimator.\nWhen the subsystems have only one global mission that needs to be accomplished (as opposed to local missions of the subsystems)\, one might think of better ways to exploit the existence of mutually cooperating subsystems. As the performance of each subsystem is n ot an issue\, but\, rather\, the accomplishment of the global mission\, ea ch subsystem can relinquish the optimality of its own estimator\, such tha t the global performance of the entire system would be optimized – at th e cost of attaining sub-optimal performance by the local estimators. We ca ll this cooperation strategy Altruism\, taking after the well-known phenom enon exhibited in nature. Altruism has been used in sociology and in game theory to describe strategies that individuals would use in order to impro ve the chances of their species to strive.\nIn this seminar we will presen t two approaches for altruistic cooperation in the problem of parameter es timation by two cooperative estimators. In the first approach\, termed het erarchical cooperative estimation\, both estimators behave altruistically\ , sacrificing their own estimation performance for the purpose of improvin g global estimation performance. In the second approach\, termed hierarchi cal cooperative estimation\, one subsystem behaves egoistically (optimizin g its own estimation performance) while the other behaves altruistically. When the underlying distribution is Gaussian\, explicit results are obtain ed and demonstrated using a numerical example. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-506@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20150903T163000 DTEND;TZID=Asia/Jerusalem:20150903T173000 DTSTAMP:20230603T192452Z URL:https://aerospace.technion.ac.il/events/small-aero-engine-design/ SUMMARY:Small Aero-engine Design DESCRIPTION:Lecturer:Prof. Junqiang ZHU\n Faculty:The Institute of Thermoph ysics\n Institute:The Chinese Academy of Science\n Location:Classroom 165\ , ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Market requirements for business\, commuter and unmanned aircrafts gen erally lead to compact\, low cost and fuel efficient small aero-engines. D esign and technology requirements for small aero-engines\, compared to the large ones used on most commercial aircrafts\, are quite challenging. Res ulting compressors and turbines normally have high pressure ratio and stag e loading\, small aspect ratio airfoils\, transonic Mach numbers\, low Rey nolds numbers and high turning blades. The small size of the turbomachiner y adds another complexity in terms of the stringent structural requirement s to achieve the desired target life as well as the manufacturing\, produc tion and assembly challenges associated with small aero-engines. This pres entation will attempt to point out these challenges and solutions based on our own experience working in the area. Thanks to the innovative key tech nologies we stored over the past three decades\, (including the non-shroud ed wider chord/swept fan blades\, advanced highly-loaded mixed-flow compre ssor\, low-emission reverse flow combustor\, highly-loaded un-cooled turbi ne\, aggressive inter-turbine transition duct and the novel lobed-mixer ex haust system\,) a brand-new\, compact\, fuel efficient small aero-engine r ated at a take-off thrust of 1000 daN was developed. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-513@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151006T163000 DTEND;TZID=Asia/Jerusalem:20151006T173000 DTSTAMP:20230603T192653Z URL:https://aerospace.technion.ac.il/events/mechanics-of-elastomers-based- on-polymer-chain-length-statistics/ SUMMARY:Mechanics of Elastomers Based on Polymer Chain Length Statistics DESCRIPTION:Lecturer:Prof. Mikhail Itskov\n Faculty:Department of Continuum Mechanics\n Institute:RWTH Aachen University\, Aachen\, Germany\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n Polymer chain length statistics as it results from the polymerization process has long been known in chemistry but has not so fa r been applied to mechanics of elastomers. In the present contribution\, t his chain length statistics is incorporated into a full network model. The free energy of such a network results from the integral of single chain e nergies over the unit sphere. The so derived multi-scale model is able to describe not only the elastic behavior but also inelastic effects peculiar to filled rubbers. These are\, in particular\, the Mullins effect\, perma nent set and strain induced anisotropy. Special attention is focused to mo delling of rubbers reinforced by carbon nanotubes. The carbon nanotubes in troduce additional cross-linking into the network and by this means influe nce the probability density function of chain lengths. Model predictions d emonstrate good agreement with experimental data. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-514@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151021T163000 DTEND;TZID=Asia/Jerusalem:20151021T173000 DTSTAMP:20230603T192715Z URL:https://aerospace.technion.ac.il/events/plume-modeling-of-a-camila-hal l-thruster-cluster/ SUMMARY:Plume Modeling of a CAMILA Hall Thruster Cluster DESCRIPTION:Lecturer:Matteo Laterza\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n The present work focuses on plume interactions in a conv ergent Hall thruster cluster for thrust vectoring. The analysis is done th rough a numerical model\, using a custom hybrid- PIC code with Monte Carlo Collisions for ion-neutral interactions. The setup consists in two thrust ers positioned at 10cm separation\, each with a 10° convergence angle. In order to provide thrust vectoring\, the ion current is changed by ±20% relatively to nominal.\nA combined simulation is compared with stand-alone simulations of the two thrusters.\nThe comparison shows not only the defl ection of high-angle charge-exchange ions\, but also deviations of the mai n plume. A non-axisymmetric divergence model is developed\, showing total divergence on the convergence plane to be smaller than single thruster div ergence\, contrary to what would be expected. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-38@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151021T183000 DTEND;TZID=Asia/Jerusalem:20151021T193000 DTSTAMP:20221030T083412Z URL:https://aerospace.technion.ac.il/events/gvahim-excellence-program-cere mony-2/ SUMMARY:“Gvahim” excellence program ceremony DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Library Classr oom (no. 165)\n Zoom: \n Abstract: \n Details: Scholarships and certificat es for the students of “Gvahim” excellence program\, for the 2014-2015 academic year.\nInvited: The Program's students and their families\, Facu lty members\, B.Sc. students and colleagues from the Aerospace Industry .\ nFor registration\, please see:\n\n CATEGORIES:Events LOCATION:Library Classroom (no. 165) END:VEVENT BEGIN:VEVENT UID:0-505@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151026T163000 DTEND;TZID=Asia/Jerusalem:20151026T173000 DTSTAMP:20230603T192437Z URL:https://aerospace.technion.ac.il/events/home-manufacturing-or-finding- out-that-you-have-too-much-spare-time/ SUMMARY:Home Manufacturing - or Finding Out That You Have Too Much Spare Ti me DESCRIPTION:Lecturer:Nadav Katzman\n Faculty:\n Institute:Rafael / MOA\n Lo cation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The lecture describes the process of combining a hobby project and home manufacturing techniques to create a home built UAV system (ground station and drone for the FPV hobby).\nThe project is comp rised of subsystems made from scratch (at home) as well as integrated open source / open hardware modules. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-519@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151104T163000 DTEND;TZID=Asia/Jerusalem:20151104T173000 DTSTAMP:20230603T193028Z URL:https://aerospace.technion.ac.il/events/long-term-satellite-cluster-fl ight-using-differential-drag/ SUMMARY:Long-term Satellite Cluster Flight Using Differential-Drag DESCRIPTION:Lecturer:Ohad Ben-Yaacov\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n One of the key issues in future space technologies is t he relative position control of a satellite cluster\, known as cluster fli ght. Cluster flight entails maximal and minimal inter-satellite distance c onstraints\, in order to prevent an unacceptable drift and avoid collision s.\nThe purpose of this research is to enable fuelless cluster flight by u sing differential-drag. This ability will render the thrusters unnecessary \, which will constitute a breakthrough in the field of cluster flight. To that end\, nonlinear differential drag-based controllers suitable for imp lementation in long-term missions were developed\, for a cluster consistin g of multiple modules. Numerical simulations show promising performance of the maximal distance controller. The minimal distance controller successf ully prevents the cluster from colliding. These algorithms are planned to be implemented on-board the Space Autonomous Mission for Swarming and Geo- locating Nanosatellites (SAMSON).\nSince any drag-based control algorithm must cope with significant uncertainties\, the closed-loop system performa nce was examined through a covariance analysis. The method used for uncert ainty quantification is the Linear Covariance Analysis.\nFinally\, a new a nalytical method for calculating the satellite projected cross-sectional a reas and concomitant torques was developed. The knowledge of this area is essential for approximating the forces and torques induced by atmospheric drag and solar radiation pressure\, and it is also required for implementi ng various attitude control modes. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-520@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151111T163000 DTEND;TZID=Asia/Jerusalem:20151111T173000 DTSTAMP:20230603T193049Z URL:https://aerospace.technion.ac.il/events/development-of-satellite-clust er-flight-algorithms-under-thrusting-errors/ SUMMARY:Development of Satellite Cluster Flight Algorithms Under Thrusting Errors DESCRIPTION:Lecturer:Michal Jashinski\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n One of the most widely considered topics in satellite cluster flight is the control of relative positions among satellites\, ref erred to as cluster keeping. In general\, satellite cluster keeping is aim ed at keeping the satellites in a specific range of distances. In order to maintain relative distances within given bounds\, maneuvers are required. Fuel consumption should be minimized in order to decrease mass. However\ , in practical situations\, thrust parameters are often uncertain. Errors can occur in the magnitude of the thrust as well as in its direction. Thes e errors are often caused by the uncertainty of operating in the space env ironment. Moreover\, the on-board sensors used for thrust measurements are noisy and biased. These effects may seriously jeopardize the cluster flig ht mission on the long term.\nThe main purpose of this research is to robu stify cluster control methods under thrusting errors and uncertainties\, a nd minimize the effect of thrusting errors and noise on the evolution of r elative distances and on the consumption of fuel. In particular\, this res earch develops algorithms that minimize the fuel consumption during the ma neuver as well as minimize the time of the maneuver in spite of thrusting errors and noise. An inverse dynamics controller was implemented\, using m ean orbital elements feedback\, while an adaptive control scheme was used for the thrust pointing error reduction in order to obtain optimality in t erms of fuel consumption and operation time.\nIn order to verify the perfo rmance of the cluster keeping controller under these conditions\, a Kalman Filter was designed for estimating the mean elements. A comparison betwee n the results with and without noise are presented. A Monte-Carlo simulati on results are also presented in order to show the convergence of the erro rs created by noise. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-490@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151118T163000 DTEND;TZID=Asia/Jerusalem:20151118T173000 DTSTAMP:20230603T192014Z URL:https://aerospace.technion.ac.il/events/fictitious-sources-method-for- noise-level-analysis-from-an-aircraft-flying-at-a-given-altitude-above-a-g round-with-variable-impedance-and-topography/ SUMMARY:Fictitious Sources Method for Noise Level Analysis from an Aircraft Flying at a Given Altitude Above a Ground with Variable Impedance and Top ography DESCRIPTION:Lecturer:Yohan Kamoun\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The analysis of noise level emanating from a distant sourc e is needed in a number of applications\, most notably in environmental en gineering. The sound pressure level (SPL) distribution is desired\, e.g.\, due to the acute effects of sound on community. To this end\, one has to solve a typically large-scale acoustics problem: a moving source over grou nd with given impedance and topography.\nSince the human hearing bandwidth is quite wide\, one has to repeatedly solve the Helmholtz equation in the upper half space for many different wave lengths\, with given impedance b oundary condition imposed on the ground. To this end\, an efficient Helmho ltz equation solver must be used.\nIn recent years\, fictitious source met hods (FSM) have been developed and applied for various problems such as ac oustic and electromagnetic wave problems. For a flat ground with a zero or infinite impedance\, basic fictitious source implementation can easily gi ve a semi-analytical solution to the Helmholtz problem using the mirror im age method. For a variable impedance or for ground with given topography\, the problem becomes much more complex\, and a numerical solution is requi red. The use of the FSM was previously proven to be efficient for the case of a flat ground with a constant impedance.\nIn this Seminar we will pres ent an extension to the previous work in the following main aspects:\n\n\n The ground impedance may be a function of location.\n Topography: the gro und may be non-flat\n\nIn contrast to the previous works\, where only the residual was calculated\, it is now possible to evaluate the true error ge nerated by the fictitious source method using a dedicated algorithm. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-491@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151125T163000 DTEND;TZID=Asia/Jerusalem:20151125T173000 DTSTAMP:20230603T192032Z URL:https://aerospace.technion.ac.il/events/tracking-a-non-cooperative-tar get-using-a-real-time-stereovision-based-control-law/ SUMMARY:Tracking a non-cooperative target using a real-time stereovision-ba sed control law DESCRIPTION:Lecturer:Tomer Shtark\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Tracking a non-cooperative target is an important challeng e in the field of robotics due to the fact that most targets are unknown a nd unspecified. This is especially true in unfamiliar environments. The us e of stereovision allows robots to passively scan large areas and to estim ate the relative position\, velocity and shape of the objects they recogni ze. These properties are valuable and can be used to further investigate t he scanned objects and determine their structure.\nThis research is an exp erimental effort\, in which non-cooperative target tracking methods using stereovision measurements were developed and evaluated. The experiments we re conducted in the Distributed Space Systems Laboratory at the Technion. The algorithm which was developed in this research with the use of stereov ision allows the estimation of the relative position and velocity of the t arget\, while a line-of-sight control algorithm utilizes the measurements and the motion of the target to keep the target within the field of view u sing real-time processing. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-493@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151130T163000 DTEND;TZID=Asia/Jerusalem:20151130T173000 DTSTAMP:20230603T192108Z URL:https://aerospace.technion.ac.il/events/mechanics-of-squishy-materials / SUMMARY:Mechanics of Squishy Materials DESCRIPTION:Lecturer:Tal Cohen\n Faculty:Department of Mechanical Engineeri ng\, MIT\n Institute:School of Engineering and Applied Sciences\, Harvard\ n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In this seminar I will address some fundament al problems in the nonlinear mechanics of soft and biological materials\; (i) the geometrically unique phenomenon of elastic fingering\, a rate-inde pendent instability observed at large strains\, (ii) the ubiquitous phenom enon of creasing\, which in recent years has been indicated as a distinct mode of instability from wrinkling\, (iii) the effect of viscoelasticity i n dynamic cavitation\, and (iv) the modeling of chemo-mechanically coupled swelling and surface growth of materials\, in absence of a natural refere nce configuration. I will show how the theoretical models are able to capt ure the essential features of these phenomena\, in comparison with numeric al simulations and experimental observations\, and will discuss some ongoi ng efforts to apply the models experimentally to measure the material prop erties of biological tissue. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-502@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151202T163000 DTEND;TZID=Asia/Jerusalem:20151202T173000 DTSTAMP:20230603T192334Z URL:https://aerospace.technion.ac.il/events/small-horizontal-axis-wind-tur bine-blade-and-control-system-redesign-testing-and-evaluation-for-urban-en vironment/ SUMMARY:Small Horizontal Axis Wind Turbine Blade and Control System Redesig n\, Testing and Evaluation for Urban Environment DESCRIPTION:Lecturer:Gandelman Roman\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n Small wind turbines located in urban environment\, ofte n suffer from low wind velocity regime and high wind fluctuation.\nThe low wind regime\, leads to increase in blades idle time\, a period where no p roduction of power is maintained due to the low torque on the blades.\nThe high wind fluctuation leads to suboptimal wind turbine working points\, a s the blades RPM (rounds per minute) is not in its optimal point.\nIn the present work the problem of low torque in low wind velocity is solved by m ulti variable torque and power optimization of wind turbine blades geometr y in low wind velocity by numerical optimization based on BEM (blade eleme nt momentum theory) a method for evaluating blade performance by combining momentum theory with blade element theory.\n\nThe problem of suboptimal w orking point in fluctuating wind is dealt by a new and cheap control metho d based on switching the load by a solid state relay (SSR).\nSwitching the load leads to control of the rotor acceleration/deceleration and so acqui ring the wanted optimal RPM working point.\n\nThe control algorithm and su itable control hardware were implemented in hardware with national instrum ent controllers (NI) and software (LabVIEW) and tested with commercial win d turbine in the lab and in real wind conditions.\nSystem design\, tests a nd results will be shown in these seminar. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-503@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20151230T163000 DTEND;TZID=Asia/Jerusalem:20151230T173000 DTSTAMP:20230603T192352Z URL:https://aerospace.technion.ac.il/events/investigation-of-the-behavior- of-damaged-aluminum-panel-under-shear-loads-reinforced-by-composite-patche s-a-new-engineering-approach/ SUMMARY:Investigation of the Behavior of Damaged Aluminum Panel Under Shear Loads\, Reinforced by Composite Patches – A New Engineering Approach DESCRIPTION:Lecturer:Yuri Simanovskii\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n Aging metallic aircraft\, manufactured in the early 70 's\, are still being operated around the world\, and are subjected to new types of damage\, appearing in new locations on the aircraft. In past year s\, the use of composites has increased for Aluminum aircraft components. Various studies substantiated these repairs to be effective from durabilit y point of view and evaluated the effect of plies application sequence\, o rientation sequence\, effect of stress intensity factor and more. However\ , all those studies focused on simple tensile loading.\nForward and center sections of a combat aircraft fuselage contain a skin\, which plays a maj or role in load transferring\, usually due to torsion originated by fusela ge bending. The present research aims at studying the effect of the above mentioned parameters on composite repair patch for a panel\, subjected to shear loads. The study is based on a new approach of finite element modeli ng\, consisting of 2D and 3D merged elements. Correspondingly\, the model is parametrically analyzed for strength and buckling\, as a function of pa tch size\, overlaps\, and sequences of plies. The analysis is then substan tiated by a dedicated set of experiments on typical representative element s. Based on the test results\, the accuracy of the finite element model wa s evaluated and thus validating the method of patch repair. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-496@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160113T163000 DTEND;TZID=Asia/Jerusalem:20160113T173000 DTSTAMP:20230603T192158Z URL:https://aerospace.technion.ac.il/events/dynamic-aeroelastic-simulation -of-the-deployment-process-of-a-wing-with-variable-sweep-angle/ SUMMARY:Dynamic Aeroelastic Simulation of the Deployment Process of a Wing with Variable Sweep Angle DESCRIPTION:Lecturer:Aviv Romm\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n New challenges in aerodynamic design of flight vehicles are s ometimes met by changing the wing sweep angle during flight. Simulations o f the wing deployment or folding process should include aeroelastic dynami c loads analysis for structural and mechanical design. The presented work expands common aeroelastic procedures to simulate the morphing process usi ng the Increased Order Modeling approach.  The analyzed case is response to gust excitation during rapid change of the wing sweep angle.  A freque ncy-domain dynamic gust response is first performed for a nominal sweep an gle with the wing and body components represented by separate model coordi nates that are coupled to satisfy the interface displacement compatibility .  A time marching simulation is then performed to modify the nominal res ponse in a way that takes into account the changing external excitation\, structural and aerodynamic effects. Each time step involves modifications of the interface compatibility constraints\, the unsteady aerodynamic forc e coefficients and the gust incidence angles\, using a previously acquired database.  The process returns to frequency-domain formulation for final calculation of the structural response and dynamic loads. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-504@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160120T163000 DTEND;TZID=Asia/Jerusalem:20160120T173000 DTSTAMP:20230603T192420Z URL:https://aerospace.technion.ac.il/events/spray-formation-by-homogeneous -flash-boiling/ SUMMARY:Spray Formation by Homogeneous Flash Boiling DESCRIPTION:Lecturer:Moti Levy\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Injection systems are integrated in a variety of applications including fuel injection systems\, painting and coating processes\, medic al inhalers and more. In some applications\, and particularly in fuel inje ction systems\, the size and size distribution of the droplets are extreme ly important properties. For example\, in jet engines and internal combust ion engines the droplet's diameter affects the combustion performances\; s maller diameter usually means better combustion efficiency and reduced air pollution. Additionally\, since even small amount of large droplets incre ase the pollutants emission and reduce the efficiency\; the size distribut ion is also important. There are various injecting methods to produce a fi ne spray that contains small and uniform droplets\; in most of them there is a use of the fluid energy (plane or swirl atomizers)\, an added gas ene rgy (air blast and air assist atomizers) or mechanical energy (rotary or s linger atomizers) to shatter the liquid jet into fine spray. One of the mo re effective methods is to inject the fluid under suitable conditions to a ttain flash boiling atomization\; i.e. injecting a pure liquid or a mixtur e under initial conditions that ensure an evaporation of the liquid or at least one of the components in a mixture during the rapid depressurization caused by the expansion in the orifice. In a binary mixture for example\, a high vapor pressure propellant might be dissolved into a low vapor pres sure solvent in order to produce rapid evaporation of the propellant durin g the depressurization through the orifice\; the rapid evaporation of the propellant disintegrates the solvent into the desired fine spray.\nThe maj ority of the studies in this field deal with the most common case in which the bubbles are formed in preferred sites on the orifice walls or near co ntaminants (heterogeneous nucleation). Studies dealing with homogeneous nu cleation\, in which the bubbles are formed in the entire bulk\, are quite rare although finer spays are anticipated since the typical bubble formati on rate in the case of homogeneous regime is much higher. The current stud y deals with homogeneous flash boiling through a plane orifice. The spray properties of pure liquid and binary mixture were characterized experiment ally\, under variety injecting conditions (injecting temperature and press ure) and a wide range of propellant mass concentration. Also\, the border line between the two regimes was examined. Additionally\, since the major ity of the studies deal with the heterogeneous case\, there are neither su itable correlations nor analytical estimations for the typical droplets' d iameter under homogeneous nucleation regime. In the current work an analyt ical model has been developed to estimate the characteristic droplet diame ter in the spray for flash boiling atomization. One significant conclusion is that under homogeneous flash boiling\, remarkably small and uniform dr oplets are achieved\; therefore by using this relatively simple method ext remely fine sprays are obtained comparing to the other methods. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-497@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160201T163000 DTEND;TZID=Asia/Jerusalem:20160201T173000 DTSTAMP:20230603T192212Z URL:https://aerospace.technion.ac.il/events/laminar-backward-facing-step-f low-with-wavy-surface/ SUMMARY:Laminar Backward Facing Step Flow with Wavy Surface DESCRIPTION:Lecturer:Hilla Tor\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Flow separation and reattachment are widespread in engineerin g in general\, and in aeronautics in particular. One of the issues that co ncern the researchers over the years is the possibility to control the flo w separation zone and the reattachment point location. In the second half of the 20th century\, the possibility of replacing rigid walls with wavy s urfaces was examined. Results of previous studies indicate that adding a w avy surface can delay the transition of the flow from laminar to turbulent .\nThe flow over a backward facing step is a fundamental model of flow sep aration. In this study\, the flow over a backward facing step with a wavy surface was examined. The effect of the frequency and amplitude of the wav y surface on the drag force\, the flow stability for small disturbances an d on the location of the reattachment point were studied numerically. The results show that the viscus drag force is increased. The location of the reattachment point and the stability of the flow are also influenced by th e choice of the surface parameters. It was found that the wavy surface amp litude and frequency that improve the flow stability also increase the dra g force. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-495@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160203T163000 DTEND;TZID=Asia/Jerusalem:20160203T173000 DTSTAMP:20230603T192142Z URL:https://aerospace.technion.ac.il/events/cooperative-and-networked-navi gation/ SUMMARY:Cooperative and Networked Navigation DESCRIPTION:Lecturer:Prof. Demoz Gebre-Egziabher\n Faculty:\n Institute:Uni versity of Minnesota\, Twin Cities Campus\, USA\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Cooperative or networked navigation are terms used to describe an appro ach whereby members of a community (or network) exchange information to ge nerate a navigation solution of higher quality than would have been possib le if each had operated alone.  There are many application in aerospace w here cooperative navigation holds the promise of enabling new capabilities or enhancing existing ones.  Examples capability enhancements in the ope ration of transport aircraft\, small UAVs and CubeSat on deep-space missio ns are described.    As will be shown\, there are many technological and algorithmic challenges that must be addressed before networked navigation concepts become practical.  One of the algorithmic challenges had to do with the design of suitable decentralized estimation algorithms.  Challen ges associated with decentralized estimation are discussed and solutions t o deal with them are proposed. Flight tests results from community of smal l UAVs operating in a GNSS/GPS-denied environment is used to validate perf ormance of the proposed algorithms. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-489@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160217T163000 DTEND;TZID=Asia/Jerusalem:20160217T173000 DTSTAMP:20230603T191958Z URL:https://aerospace.technion.ac.il/events/on-the-annual-cycle-of-a-hover ing-hummingbird-an-aerodynamic-and-fluid-mechanics-perspective/ SUMMARY:On the Annual Cycle of a Hovering Hummingbird: An Aerodynamic and F luid Mechanics Perspective DESCRIPTION:Lecturer:Yonathan Achache\n Faculty:Technion Autonomous Systems Program\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n The diverse hummingbird family (Trochilidae) has uniqu e adaptations for nectarivory\, among which is the ability to sustain hove r feeding. As hummingbirds mostly feed while hovering\, it is crucial to m aintain this ability throughout the annual cycle and especially during fli ght feather moult\, when feathers are missing from the wing structure. The presented research will focus on the wing of Calypte anna\, a common humm ingbird species in western North America\, which consists of ten primary f light feathers whose deficit during moult may strongly affect wing aerodyn amics.\nThe goal of this work is to quantify the aerodynamic characteristi cs and flow mechanisms during the wing's annual cycle. Birds usually moult their feathers in a deterministic sequence that may have aerodynamic\, ph ysiological and behavioural ramifications. Unsteady aerodynamic loads and flow field measurements are correlated over a complete dynamically scaled Anna's wing model and several wing geometries that follow the feather repl acement sequence characterising a natural moult cycle. Using dynamic simil arity\, wing models were tested in water-glycerin solutions at biologicall y relevant Reynolds numbers and various angles of attack.\nResults were ta ken over a model of a complete wing in order to depict the baseline aerody namic characteristics and flow mechanisms involved. Unsteady vorticity con centration evolved from the wing's leading-edge differs in both size and e xtent from attached vorticity structures typically found over insects\, wh ich themselves operate at Reynolds numbers which are two orders of magnitu de smaller than those of hummingbirds. Estimation of the complete wing per formance suggests it yields comparable lift coefficients and higher lift-t o-drag ratios to those found over insects.\nMeasurements taken at several moult stages suggests that the wing's integrity in the medial and leading- edge region affects the flow field considerably such that lift production drops disproportionately higher in relation to the loss of wing area\, whi ch explains why the leading feathers of the wing are essential to obtain h igh lift capacity during hovering. Furthermore\, specific-power analysis s uggests a distinct link to behavioural repertoire and mass reduction chara cterising moulting hummingbirds. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-498@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160224T163000 DTEND;TZID=Asia/Jerusalem:20160224T173000 DTSTAMP:20230603T192226Z URL:https://aerospace.technion.ac.il/events/cooperative-guidance-law-for-i ntra-salvo-tracking/ SUMMARY:Cooperative Guidance Law For Intra-salvo Tracking DESCRIPTION:Lecturer:Nadav Balhance\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n The use of multiple interceptors against a single target is an effective way of increasing the chances of success of an intercept. The basic method is salvo shooting\, in which each interceptor is indepen dently guided toward hitting the target.  With the growth of computers pr ocessing power and the developments in communication capabilities of moder n interceptors\, the alternative approach of using interceptors that coope rate with each other in order to complete the common intercept mission is becoming a more promising and attractive solution. In order to cooperate\, the interceptors should communicate. The communication ability among the interceptors is strongly related to the geometric configuration of the eng agement\, especially if the communication is achieved by the use of unidir ectional antennas.\nIn this seminar we will present three cooperative guid ance algorithms for the case where two interceptors pursue a single target \, while constraining an additional geometric condition. The geometric con dition is to preserve the relative look angle between the interceptors aro und some constant reference values during the engagement. This kind of geo metric condition enables the cooperating interceptors to communicate with each other even with the use of unidirectional antennas.\nWe will begin th e talk with some background and presentation of the guidance problem\, fol lowed by a formulation of the guidance problem as a linear quadratic optim al control problem. We will then present its solution considering two situ ations: when reference values for the relative look angles are given\, and when they are free and can be chosen to improve the performance of the gu idance law. To summarize the talk\, we will present numerical examples\, w hich demonstrate that applying the proposed guidance algorithms\, enables to achieve the additional geometric condition without substantially affect ing the miss distance and with a reasonable control effort. A comparison b etween the proposed guidance algorithms will be presented as well. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-492@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160307T163000 DTEND;TZID=Asia/Jerusalem:20160307T173000 DTSTAMP:20230603T192049Z URL:https://aerospace.technion.ac.il/events/hypersonic-aeroelasticity-and- aerothermoelasticity-a-multiphysics-challenge/ SUMMARY:The Hanin Lecture - Hypersonic Aeroelasticity and Aerothermoelastic ity - a Multiphysics Challenge DESCRIPTION:Lecturer:Prof. Peretz Friedmann\n Faculty:Department of Aerospa ce Engineering\n Institute:University of Michigan\n Location:Classroom 165 \, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details : \n A concise review of a series of studies on aeroelasticity and aerothe rmoelasticity of hypersonic vehicles conducted during the last 18 years\, by the author and his students will be presented. These studies have focus ed on a few basic configurations: a typical section\, a panel\, a low aspe ct ratio wing and an idealized model of an entire hypersonic vehicle.  In these studies the complexity of the problems considered was progressively increased demonstrating the multiphysics nature of hypersonic aerothermoe lasticity.  This sustained activity has recently culminated in the develo pment of an integrated aerothermoelastic computational framework that gene rates a high fidelity model. The framework consists of a Navier-Stokes aer odynamic solver based on a modified version of the Stanford University mul tiblock (SUmb) code\, a finite element structural solver for moderate defl ection of composite doubly-curved shallow shell with thermal stress\, and a finite element thermal solver for heat transfer in composite shallow she lls with nonlinear material properties. The solvers are coupled using a pa rtitioned scheme. The aeroelastic behaviors of 2D and 3D panels are invest igated using the computational frame-work. The 3D effect and Reynolds numb er is found to have significant influence on the critical flutter paramete r\, and limit cycle amplitude. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-501@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160307T163000 DTEND;TZID=Asia/Jerusalem:20160307T173000 DTSTAMP:20230603T192320Z URL:https://aerospace.technion.ac.il/events/the-3rd-annual-professor-singe r-memorial-lecture-morphing-composites-for-aerospace-applications/ SUMMARY:The 3rd Annual Professor Singer Memorial Lecture - "Morphing Compos ites for Aerospace Applications" DESCRIPTION:Lecturer:Prof. Paul Weaver\n Faculty:Department of Aerospace En gineering\n Institute:University of Bristol\n Location:Classroom 165\, gro und floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n I t is known that a structure should resist loads without failure. For struc tures that contain humans\, i.e. houses\, boats\, cars\, aircraft etc.\, t hey do not stretch (or deform) a great deal and those that are required to move around should be lightweight to keep fuel costs down e.g. aircrafts and super-lightweight to overcome gravity (e.g. rockets\, spacecraft).\nTh is seminar explores the possibility of using unusual properties of materia ls with some additional nonlinear geometric behavior to either reduce mass or to achieve a significant shape change (morphing) of a structure. Examp les are drawn from aircrafts\, helicopters\, wind turbine blades\, cars an d from nature. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-36@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160309T080000 DTEND;TZID=Asia/Jerusalem:20160309T090000 DTSTAMP:20221030T083413Z URL:https://aerospace.technion.ac.il/events/the-56th-israel-annual-confere nce-on-aerospace-sciences/ SUMMARY:The 56th Israel Annual Conference on Aerospace Sciences DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Tel Aviv/Haifa \n Zoom: \n Abstract: \n Details: \nThe Israel Annual Conference on Aerosp ace Sciences\, spanning several generations\, is an important annual event on the calendar of the aerospace community in Israel. Taking part in this yearly event are engineers\, scientists and experts in the field of aeron autics and astronautics\, representing well-known local aerospace agencies and industries\, as well as participants from major research centers worl dwide. The conference hosts a unique undergraduate student competition on aerospace research and design.\n\n\n \;\n CATEGORIES:Events LOCATION:Tel Aviv/Haifa END:VEVENT BEGIN:VEVENT UID:0-500@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160321T163000 DTEND;TZID=Asia/Jerusalem:20160321T173000 DTSTAMP:20230603T192302Z URL:https://aerospace.technion.ac.il/events/distance-constrained-formation -tracking-control-of-multi-agents-systems/ SUMMARY:Distance-Constrained Formation Tracking Control of Multi-agents Sys tems DESCRIPTION:Lecturer:Oshri Rozenheck\n Faculty:Technion Autonomous Systems Program\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n In recent years\, there has been an increasing number o f contributions dealing with the control of multiple agent formations. Of the many control strategies for formation control\, distance-constrained f ormation control aims at maintaining inter-agent distances and utilizes re lative measurements (i.e.\, distances and relative-positions) to generate the control action. In this work\, we consider a collection of agents task ed with maintaining a distance constrained formation\, where one agent in the ensemble is also designated as a leader and is subjected to an externa l velocity reference command.\nThe controller can act as the velocity inpu t or the acceleration input depending on the mathematical model. We begin with a simple single integrator model without velocity reference by derivi ng the formation error dynamics and showing stability. By adding a velocit y reference command to the leader and in the absence of any additional con trol action\, the standard rigidity based formation stabilization solution s will exhibit a steady state formation error. As we try to address this p roblem we also reveal more interesting relations between the upper bound o f the steady state error and the graph properties. Our approach is to comb ine gradient based formation controller with a proportional and integral ( PI) control to eliminate this steady-state error. We show that such a sche me preserves the stability properties of the formation error dynamics as w ell as properties of the networked system’s centroid. We then explore th e properties of double integrator model and show that using rigidity based formation controller only is not enough to ensure stability. By adding a velocity-based decentralized control we were able to reach velocity consen sus and assure formation stability. As we want the system to also follow a n external reference velocity\, a simple inner-loop controller is implemen ted on the leader to ensure velocity tracking. Numerical simulations are s hown to illustrate the theoretical results. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-488@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160330T163000 DTEND;TZID=Asia/Jerusalem:20160330T173000 DTSTAMP:20230603T191935Z URL:https://aerospace.technion.ac.il/events/club-%d7%9e%d7%93%d7%91%d7%a8% d7%99%d7%9d-%d7%91%d7%90%d7%95%d7%99%d7%a8-2/ SUMMARY:Club "מדברים באויר" DESCRIPTION:Lecturer:Prof. Pini Gurfil and Asst. Prof. Beni Cukurel\n Facul ty:Department of Aerospace Engineering\n Institute:Technion – Israel Ins titute of Technology\n Location:Classroom 165\, ground floor\, Library\, A erospace Eng.\n Zoom: \n Abstract: \n Details: \n Prof. Pini Gurfil's lect ure will be on the topic:\n\nThe Distributed Space Systems Lab  -  "המ עבדה למערכות חלל מבוזרות"\nThe Distributed Space Syst ems lab performs research in astrodynamics\, guidance\, navigation and con trol of multiple-satellite systems\, with emphasis on cluster flight of na nosatellites. In this talk\, we will present some of these research areas. In particular\, we will show some research highlights in the areas of rel ative satellite motion\, space robotics\, vision-aided space navigation\, and the SAMSON project\, which is a triple nanosatellite mission that will be launched in 2017.\nAsst. Prof. Beni Cukurel's lecture will be on the t opic:\n\nThe Turbomachinery and Heat Transfer Lab  -  "המעבדה לט ורבו-מכונות ומעבר חום"\nThe Turbomachinery and Heat Tran sfer Laboratory conducts research and development in the field of micro ga s turbines for propulsion and power generation applications. The Turbomach inery Center is intended to serve as a center of knowledge for the academi a\, as well as the industry. In parallel\, the laboratory leads experiment al heat transfer research\, and conducts advanced measurement technique de velopment. The discussed research activities will include versatile micro turbo-fan engine\, optimization of smart-grid equipped with micro-gas turb ines\, advanced micro-turbine research facility\, acoustically enhanced he at exchangers\, thermophone sound production\, multispectral infrared ther mography and novel hot-wire anemometry methods. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-499@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160404T163000 DTEND;TZID=Asia/Jerusalem:20160404T173000 DTSTAMP:20230603T192244Z URL:https://aerospace.technion.ac.il/events/a-look-into-space/ SUMMARY:A look into space DESCRIPTION:Lecturer:Aviv Kanelbaum\n Faculty:Space Group\n Institute:Israe l Aerospace Industries\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n What is space and why do we want to go there? What are satellites and space- crafts and how do t hey work?\nSpace environment is much different than the environment found on Earth\, these differences\, together with the fact that it is nearly im possible to fix satellites in orbit nor to bring them back to earth poses strict constraints on the product's design\, manufacture\, assembly and te sts. On top of all these\, design must take into account the high price (u p to 100K$ per Kg) and harsh environmental conditions of the launch scenar io.\nA small number of Israeli based agents builds these wonderful machine s called satellites (including the Technion)\, IAI's MBT Space is the lead ing place in Israel for building satellites both for low earth orbits and for Geo-Synchronic orbits.\nIn order to prove the ability of the space cra ft to withstand the environmental conditions mentioned above\, space produ cts use a set of very unique facilities such as vacuum chambers\, acoustic chambers\, shakers and more.\nA review of the past\, present and future s atellites will be given together with the specific tests these space craft s must undergo before launch.\nThe main historic factors that pushed Israe l into space and the difficulties present in launching a satellite into or bit from Israel will be presented.\nA short overview of the worldwide spac e status\, civil and military\, in the present and in the future\, will be given.\nIn conclusion\, several problems and their solutions using acade mic theories will be presented and how aerospace students can be integrate d in the space industry. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-483@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160411T163000 DTEND;TZID=Asia/Jerusalem:20160411T173000 DTSTAMP:20230603T191644Z URL:https://aerospace.technion.ac.il/events/numerical-and-experimental-inv estigations-of-the-camila-hall-thruster-plume/ SUMMARY:Numerical and Experimental Investigations of the CAMILA Hall Thrust er Plume DESCRIPTION:Lecturer:Matteo Laterza\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n This work focuses on the characterization of the plume o f the CAMILA Hall thruster. A numerical model is developed and implemented in a computational code using a hybrid Particle-In-Cell scheme. A series of Langmuir probe measurements is performed in the plume at 1m downstream of the thruster. These measurements are used along with existing data to v alidate the numerical model.\nThe developed code is then used to analyze p lume behavior at different operating points. A two thruster cluster is als o simulated in different configurations to test plume interactions in conv erging clusters and to determine optimal convergence angles for thrust vec toring. It was found that the plume interactions manage to decrease plume divergence\, contrary to what expected. An optimal vectoring configuration was also found for deflection angles up to 10°. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-22@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160413T123000 DTEND;TZID=Asia/Jerusalem:20160413T143000 DTSTAMP:20221030T083415Z URL:https://aerospace.technion.ac.il/events/graduate-studies-research-day- 2/ SUMMARY:Graduate Studies Research Day DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Lobby of the m ain Faculty building\n Zoom: \n Abstract: \n Details: The annual Research Day will be held on April 13th 2016 between 12:30 and 14:30 at the Faculty of Aerospace Engineering on the ground floor of the Faculty building.\nTh e Faculty's graduate students' research will be exhibited in poster format   to undergraduate and  graduate students\, Faculty members\, candidates for graduate studies and industry representatives.\nAt the end of the day awards will be granted to the best posters.\n CATEGORIES:Events LOCATION:Lobby of the main Faculty building END:VEVENT BEGIN:VEVENT UID:0-481@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160413T163000 DTEND;TZID=Asia/Jerusalem:20160413T173000 DTSTAMP:20230603T191610Z URL:https://aerospace.technion.ac.il/events/investigation-of-nano-porous-s ilicon-based-energetic-materials/ SUMMARY:Investigation of Nano-Porous Silicon Based Energetic Materials DESCRIPTION:Lecturer:Evgenia Golda Kishilev\n Faculty:Department of Aerospa ce Engineering\n Institute:Technion – Israel Institute of Technology\n L ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n This study investigates a unique energetic mater ial based on nano-porous silicon fuel impregnated with an oxidizer. This e nergetic material is very promising due to its integration potential with MEMS systems\, which are realized using the same raw material - silicon.\n Nano-porous silicon is an inert material that can be fabricated by anodiza tion of silicon in a hydrofluoric acid solution. The inert nano-porous sil icon structure is transformed into an energetic material by impregnation o f a dissolved oxidizer into the nano-pores. The preparation method and the thermal characteristics of this energetic material applying different oxi dizers have been investigated thoroughly. Energy outputs as high as 9.3 kJ /g\, twice the value for TNT\, have been measured using Differential Scann ing Calorimeter. The energetic reaction was demonstrated by ignition of th e samples using a hot plate above 300°C\, a semi-conductor bridge device\ , and a standard ignitor. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-480@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160418T163000 DTEND;TZID=Asia/Jerusalem:20160418T173000 DTSTAMP:20230603T191554Z URL:https://aerospace.technion.ac.il/events/enhancement-of-internal-heat-t ransfer-in-low-nox-gas-turbine-combustion/ SUMMARY:Enhancement of Internal Heat Transfer in Low Nox Gas Turbine Combus tion DESCRIPTION:Lecturer:Daniel Kutikov\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Pollutant emissions from combustion systems created incr easing environmental and health concerns. Regulations controlling pollutan t emissions steadily become stricter. Nitrogen oxides (NOx) are currently regarded as the most harmful pollutants emitted during fuel-air combustion . Existing low NOx techniques all have significant drawbacks\, namely\, lo w combustion stability\, complex layout and large combustor volume. The st rict pollutant emission policies and the drawbacks of existing low NOx tec hniques motivate research on reduction of pollutant emissions from gas tur bines.\nThe formation of pollutants in combustors is strongly affected by processes of internal heat transfer and mixing by means of hot spots forma tion modification. The current research intended to investigate the impact of tangential swirl on the heat transfer and mixing in gas turbine combus tors with regard to NOx emission reduction. A novel combustor concept\, ba sed on flame cooling by pure heat transfer between the primary and seconda ry flows\, was tested in course of the research.\nA comprehensive review o f swirl-combustion interaction\, carried out in course of the research\, r evealed three major routes of swirl impact on NOx formation. The swirl imp act routes of heat transfer rate augmentation and flame elongation have a potential of NOx emission reduction\, while the swirl impact route of hot core formation may lead to NOx emission increase. These routes were invest igated at the present study by means of analytical investigation as well a s heat transfer and combustion experiments using a small-scale gas turbine combustor model. For evaluation of swirl impact\, the experiments were pe rformed for swirl flow and axial flow layouts. A novel method for convecti ve heat transfer measurements was developed in course of the experiments.\ nThe heat transfer experiments demonstrated that the increase of convectiv e heat transfer coefficient due to swirl introduction is insufficient in r egard to NOx emission reduction in gas turbine combustors. No remarkable e ffect of flow rate or temperature difference (which in a swirl flow could modify the flow pattern) on convective heat transfer coefficient was obser ved.\nThe nearly constant overall equivalence ratio in the combustion expe riments matched the most stable combustion regime and was equal to about 0 .15. The equivalence ratio in the primary zone was near unity. The combust ion experiments demonstrated an increase of NOx emission by a factor of ab out 2\, due to the introduction of swirl. This proved that the hot core fo rmation due to the swirling of the flow is dominant for gas turbine combus tors with tangential swirl. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-482@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160420T163000 DTEND;TZID=Asia/Jerusalem:20160420T173000 DTSTAMP:20230603T191629Z URL:https://aerospace.technion.ac.il/events/club-%d7%9e%d7%93%d7%91%d7%a8% d7%99%d7%9d-%d7%91%d7%90%d7%95%d7%99%d7%a8-3/ SUMMARY:Club "מדברים באויר" DESCRIPTION:Lecturer:Assoc. Prof. Tal Shima and Asst. Prof. Stephan Rudykh\ n Faculty:Department of Aerospace Engineering\n Institute:Technion – Isr ael Institute of Technology\n Location:Classroom 165\, ground floor\, Libr ary\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Assoc. Prof. Tal Shima's lecture will be on the topic:\n"Guidance of Aerial Vehicles - הנ חיית כלים אויריים"\nIn this short talk we will present some classical pursuit-evasion engagements between a single interceptor chasin g a single target\, as well as some new engagements that include more than two participants. We will present and discuss a few guidance strategies a pplicable in such aerial engagements. Some experimental work performed in our Cooperative Autonomous SYstems (CASY) lab will be presented as well.\n Asst. Prof. Stephan Rudykh's lecture will be on the topic:\n"Fantastic Mat erials and Where to find them – חומרים פנטסטיים ואיפה למצוא אותם"\nYou have probably heard of\, seen\, or used 3D prin ters to make things. Well\, that’s what we do in our Lab. We design mate rials with new functionalities: they can trap waves\, change color\; they can morph and act as artificial muscles. We learn from nature and combine these design rules with our ability to use and 3D-print synthetic material s. I will show some pictures\, no equations - you should come. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-487@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160504T163000 DTEND;TZID=Asia/Jerusalem:20160504T173000 DTSTAMP:20230603T191754Z URL:https://aerospace.technion.ac.il/events/algorithmic-advances-in-planni ng-and-control-of-robotic-systems/ SUMMARY:Algorithmic Advances in Planning and Control of Robotic Systems DESCRIPTION:Lecturer:Prof. Emilio Frazzoli\n Faculty:Department of Aeronaut ics and Astronautics & Laboratory for Information and Decision Systems\n I nstitute:Massachusetts Institute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \ n This talk addresses the problem of "anytime" control strategy synthesis for dynamical systems\, proposing a general framework based on the increme ntal refinement of a finite "concretization" of the system. We focus on th e problem of designing a plan to fulfill a given task specification while satisfying a set of safety rules\, and in particular to task specification s that become feasible only if a subset of the safety rules are violated. The proposed algorithm then computes a control law\, that minimizes the le vel of unsafety for a trajectory that satisfies the given task specificati on. This problem is motivated by an autonomous car navigating an urban env ironment while following rules of the road such as “always travel in rig ht lane” and “do not change lanes frequently\,” or UAVs planning a m ission balancing mission objectives\, rules of engagements\, and environme ntal constraints.  Ideas behind sampling based motion-planning algorithms \, such as the Probabilistic Road Map (PRM) and Rapidly-exploring Random T ree (RRT)\, are employed to incrementally construct a finite concretizatio n of the dynamics as a durational Kripke structure. In conjunction with th is\, a finite automaton that captures the safety rules is used in order to find an optimal trajectory that minimizes the violation of safety rules. It is shown that the proposed algorithm guarantees asymptotic optimality\, i.e.\, almost-sure convergence to optimal solutions. The algorithms are d emonstrated on an autonomous vehicle platform---showing perhaps for the fi rst time the applicability of formal methods to full-scale\, real-world ro botic systems. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-484@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160518T163000 DTEND;TZID=Asia/Jerusalem:20160518T173000 DTSTAMP:20230603T191659Z URL:https://aerospace.technion.ac.il/events/in-orbit-tracking-of-high-area -to-mass-ratio-space-objects/ SUMMARY:In-Orbit Tracking of High Area-to-Mass Ratio Space Objects DESCRIPTION:Lecturer:Daniel N. Brack\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n High Area to Mass Ratio (HAMR) space objects in high Ea rth orbits experience oscillations in orbit eccentricity due to the force of the Solar Radiation Pressure (SRP). These variations\, which change the orbital altitude\, render HAMR space debris a threat for high-altitude sp ace systems\, such as geostationary satellites. This threat is enhanced be cause of the limited ground-based tracking capability of high-altitude HAM R objects.\nIn this talk\, we will propose using in-orbit tracking of HAMR objects using optical systems. This approach enables in-situ estimation o f various properties of HAMR objects\, such as the specific SRP force\, wh ich subsequently provide better orbit predictions. The design of a stereos copic in-orbit HAMR object tracking system and a concomitant parameter est imation algorithm will be presented. Different design alternatives for the tracking system and algorithm will be examined as well\, and their perfor mance will be evaluated using a variety of operational scenarios. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-479@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160525T163000 DTEND;TZID=Asia/Jerusalem:20160525T173000 DTSTAMP:20230603T191541Z URL:https://aerospace.technion.ac.il/events/computation-aeroacoustics-high -order-and-low-order/ SUMMARY:Computation Aeroacoustics: High-Order and Low-Order DESCRIPTION:Lecturer:Reda R. Mankbadi\n Faculty:\n Institute:Embry-Riddle A eronautical University\, Florida\, USA\n Location:Classroom 165\, ground f loor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The fi rst attempts to predict aerodynamically-generated sound based on direct so lution of Navier-Stokes equations began in early 1990. This relatively new field has now come a long way. n. We present two examples: Reducing UAV W ing Noise: We use a high-order LES code to explore the possibility of usin g Synthetic Jet Actuators to reduce Noise. The other example is Rocket Lif t-off Noise:  To enable studying noise generated by realistic geometries\ , we adopt a Hybrid RANS-LES approach using low-order scheme on non-unifor m grid to predict the noise produced by impinging jets representing vertic al take-off of aircrafts or Rockets Lifts-off. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-472@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160608T163000 DTEND;TZID=Asia/Jerusalem:20160608T173000 DTSTAMP:20230603T191320Z URL:https://aerospace.technion.ac.il/events/topological-interlocking-a-pro mising-materials-design-principle/ SUMMARY:Topological Interlocking: A Promising Materials Design Principle DESCRIPTION:Lecturer:Yuri Estrin\n Faculty:Monash University\, Melbourne\, Australia and\n Institute:National University of Science and Technology (N UST) MISiS\, Moscow\, Russia\n Location:Classroom 165\, ground floor\, Lib rary\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n We present a nov el approach to designing materials using the topological interlocking prin ciple. Segmentation of monolithic materials into identical interlocked bui lding blocks provides the structure with enhanced resistance to crack prop agation\, high tolerance to local failures\, increased sound insulation ca pacity and other beneficial properties [1]. In addition\, different materi als can be blended within such a structure in any pattern and proportion\, which may provide it with multifunctionality. A further advantageous prop erty of topologically interlocked ensembles of blocks is the possibility t o control the stiffness of the assembly. By including in the structure act ive elements that possess shape memory\, actuation becomes possible in tha t a precipitous change of stiffness can be produced. This will be illustra ted by an assembly of osteomorphic ceramic blocks armoured with tensioning wires from a shape memory alloy (Nitinol). The constraining force imposed on the assembly through the wires governs its bending stiffness and load bearing capacity. Such a segmented plate can act as a smart structure\, wh ich changes its flexural stiffness and load bearing capacity “on demand ”\, in response to external stimuli\, such as heat generated by the swit ching an electric current on and off [2]. In another example\, platelets o f ultra-high molecular weight polyethylene (UHMWPE) embedded in an assembl y of ceramic osteomorphic blocks were used for actuation. This polymer pos sesses a large shape memory effect [3]. Heating of the platelets by passin g an electric current was shown to produce a response of the structure by stiffening and load increment. The use of biomimetic principles in the des ign of topological interlocking structures will also be discussed. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-20@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160614T123000 DTEND;TZID=Asia/Jerusalem:20170614T143000 DTSTAMP:20221030T083416Z URL:https://aerospace.technion.ac.il/events/faculty-picnic-2/ SUMMARY:Faculty Picnic DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty front lawn\n Zoom: \n Abstract: \n Details: A faculty picnic for students and fa culty members.\n CATEGORIES:Events LOCATION:Faculty front lawn END:VEVENT BEGIN:VEVENT UID:0-485@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160615T163000 DTEND;TZID=Asia/Jerusalem:20160615T173000 DTSTAMP:20230603T191716Z URL:https://aerospace.technion.ac.il/events/transition-to-turbulence-in-wa ll-bounded-shear-flows/ SUMMARY:Transition to Turbulence in Wall-Bounded Shear Flows DESCRIPTION:Lecturer:Michael Karp\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Albeit great advancement\, transition to turbulence contin ues to be an intriguing subject\, challenging many researchers worldwide. The current research covers several aspects of transition - The evolution of coherent structures\, such as counter-rotating vortex pairs and hairpin s\, observed in various transitional as well as turbulent flows is studied using a novel analytical-based numerical method for the evolution of loca lized disturbances in homogenous shear base-flows. A minimal element model capable of following the evolution of packets of hairpins is developed an d compared successfully with experiments. Finally\, an analytical model fo r transition via secondary instability of counter-rotating vortices in cha nnel flow is presented. The model utilizes separation of scales between th e slowly evolving base-flow and the rapidly evolving secondary disturbance to capture most transition stages using the multiple time scales method a nd its predictions are verified by comparison with direct numerical simula tions. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-486@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160620T163000 DTEND;TZID=Asia/Jerusalem:20160620T173000 DTSTAMP:20230603T191733Z URL:https://aerospace.technion.ac.il/events/investigation-of-the-autorotat ion-of-a-cargo-container/ SUMMARY:Investigation of the Autorotation of a Cargo Container DESCRIPTION:Lecturer:Kfir Arbel\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Carriage of external slung loads by helicopters is a common method of transporting large and heavy loads. In many cases slung loads th at are connected to the helicopter through a swivel\, tend to develop stea dy rotation as a result of the aerodynamic loads that act on them during f light. This phenomenon is called autorotation. Previous research has shown that autorotation may be very beneficial since in many cases it stabilize s the slung load. Without rotation the same load may become unstable\, exh ibiting large pendulum vibrations that endanger the helicopter. Wind tunne l and flight tests have shown that the autorotation phenomenon depends on the: geometry of the load\, its mass distribution\, the orientation of the load relative to the incoming flow\, and other parameters. There is not a simple method of predicting the autorotation speed of a body when the abo ve parameters are known. Detailed CFD calculations predict the phenomenon\ , but the differences between the predicted autorotation speed and measure d speed are significant in many cases.\nPrevious studies at the Technion s howed good agreement between the autorotation speed of actual slung loads during flight tests and small wind tunnel models. In those tests the model s were hung from the tunnel ceiling and performed pendulum motions as well as autorotaion. The goal of the present research is to study the autorota tion of box-like models during wind tunnel tests. During the tests rotatio n about a fixed axis is the model sole degree of freedom. The angle of rot ation is measured continuously and the angular speed and acceleration are calculated. In addition the forces and moments that act on the model durin g autorotation are also measured.\nThe seminar will start with a short rev iew of previous research on the autorotation phenomenon. Then the wind tun nel test set up and test techniques will be described. Selected results wi ll be presented and discussed. These results will include autorotation of different models at different wind tunnel speeds. An effort to describe th e phenomenon by a simple empirical formula will also be presented and disc ussed. The presentation will end with suggestions for further research. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-474@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160622T163000 DTEND;TZID=Asia/Jerusalem:20160622T173000 DTSTAMP:20230603T191353Z URL:https://aerospace.technion.ac.il/events/ph-d-seminar-in-memory-of-prof -shmuel-and-mrs-noemi-merhav-manipulating-wave-propagation-in-soft-metamat erials-via-external-stimuli/ SUMMARY:Ph.D. Seminar in Memory of Prof. Shmuel and Mrs. Noemi Merhav - Man ipulating Wave Propagation in Soft Metamaterials via External Stimuli DESCRIPTION:Lecturer:Pavel Galich\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Recently\, acoustic metamaterials with periodic microstruc tures (referred as phononic crystals) have attracted considerable attentio n due to their remarkable properties – such as negative elastic moduli\, mass density\, and refractive index – stemming from their microstructur es. Moreover\, the ability of soft metamaterials to sustain large deformat ions opens rich possibilities for manipulating acoustic characteristics by deformation. Hence\, elastic waves can be tuned by constructing microstru ctures\, which can be further actively controlled by external stimuli\, e. g.\, by mechanical loading\, magnetic or electric fields.\nIn this talk\, we will start with the discussion of the acoustic properties of the relati vely simple homogeneous hyperelastic materials\, and then we will turn to the materials with periodic microstructures. First\, we will explore the i nfluence of the deformation induced stiffening on the propagation of small -amplitude elastic plane waves. Second\, we will show that electroactive h omogeneous materials can be utilized to achieve acoustic functionalities s uch as disentangling of pressure and shear waves by application of an elec tric field. Next\, we will proceed with the analysis of wave propagation i n highly deformable layered materials. In particular\, we will present the long wave estimates of the phase and group velocities for the waves propa gating in finitely deformed layered media. Moreover\, we will introduce th e material compositions and loading conditions producing wide complete ban d gaps (i.e. frequency ranges where neither pressure nor shear waves canno t propagate) at  low frequency ranges. Finally\, we will discuss the anis otropy of elastic wave propagation in finitely deformed fiber-reinforced c omposites. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-7@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160703T163000 DTEND;TZID=Asia/Jerusalem:20160703T173000 DTSTAMP:20221030T083417Z URL:https://aerospace.technion.ac.il/events/the-third-annual-professor-sin ger-memorial-lecture/ SUMMARY:The Third Annual Professor Singer Memorial Lecture DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Eng. Library classroom (room no. 165)\n Zoom: \n Abstract: \n Details: \n CATEGORIES:Events LOCATION:Aerospace Eng. Library classroom (room no. 165) END:VEVENT BEGIN:VEVENT UID:0-478@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160706T163000 DTEND;TZID=Asia/Jerusalem:20160706T173000 DTSTAMP:20230603T191519Z URL:https://aerospace.technion.ac.il/events/satellite-collision-awareness- and-avoidance/ SUMMARY:Satellite Collision Awareness and Avoidance DESCRIPTION:Lecturer:Elad Denenberg\n Faculty:Technion Autonomous Systems P rogram\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Spacecraft formation and cluster flight control have see n growing interest in the last decade. However\, the problem of finding th e optimal debris collision avoidance maneuver for a member of a cluster ha s received little attention. Our work explores novel optimization methods supporting the calculation of a debris evasive maneuver for a satellite wh ich is a member of a cluster. These include an improvement to the calculat ion of Time of Closest Approach (TCA)\, a new method for calculating the m aximum distance between orbiting objects and improvements to the calculati on of optimal debris avoidance maneuvers. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-466@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160711T163000 DTEND;TZID=Asia/Jerusalem:20160711T173000 DTSTAMP:20230603T191126Z URL:https://aerospace.technion.ac.il/events/on-the-conversion-of-gas-turbi ne-combustors-low-swirl-injection/ SUMMARY:On the conversion of Gas Turbine Combustors – Low Swirl Injection DESCRIPTION:Lecturer:Joseph Kalyan Raj I.\n Faculty:Department of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Loc ation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n A bstract: \n Details: \n The research work will discuss investigations into the characteristics of Low Swirl Injector (LSI) technique as a viable mod ification to be used in the conversion of liquid fuelled aero-engines to g aseous fueled gas turbines. Implementation of LSIs as an effective fuel in jection method for in-operation gas turbines opens the possibility of conv ersion of liquid-fuelled jet engines to fuel-flexible aeroderivative gas t urbine power plants. Low Swirl Injectors (LSIs) can be used for ultra-low emissions operation of gas turbines and promise to be a potential optimiza tion tool in the conversion of jet engines to aeroderivative gas turbines\ , since their implementation requires minimal modifications to the combust or geometry.\nThe present study explores the fluid dynamics aspects of an LSI system that has been studied using a variable swirl burner\, developed as a part of the study. The study included combustion experiments and col d-flow numerical simulations\, in order to determine the limits of operati on of the burner in the LSI regime. Further\, a novel swirl number has bee n developed to better characterize the low swirl characteristics of the LS I technique. The LSI swirl number looks promising towards developing a dee per understanding of the physics of the LSI method\, and opens up the poss ibility for new approaches to numerical modelling of LSI flames. The ultra -low emissions burning of LSI flames have been established in the experime nts\, thus showing with certainty that the Low Swirl Injection method has potential as a viable method for gas turbine combustor modification. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-471@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160713T163000 DTEND;TZID=Asia/Jerusalem:20160713T173000 DTSTAMP:20230603T191302Z URL:https://aerospace.technion.ac.il/events/thermodynamic-simulation-of-a- continuous-closed-loop-heated-micro-turbine-test-facility/ SUMMARY:Thermodynamic Simulation of a Continuous Closed Loop Heated Micro-T urbine Test Facility DESCRIPTION:Lecturer:Oleg Isaev\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n This incremental development project is focused around a ver satile continuously-running high-speed micro gas turbine research facility \, which is capable of matching full engine similarity conditions includin g pressure loading (synonymous with Mach number)\, rotational speed\, Reyn olds number\, as well as blade to gas temperature ratios. Towards predicti ng the aerodynamic and thermal conditions created on the test article\, th e current work describes the thermodynamic steady-state simulation of the closed-loop system that consists of a compressor\, a pressure vessel\, an electric heater\, a test turbine\, a dynamometer\, pressure drop valves an d an aftercooler. These subcomponents have inter-dependent performance par ameters. Based on an explicit time-marching algorithm\, virtual experiment s are conducted in the system model to map the performance of the micro tu rbine as it is influenced by the independent control parameters (rotationa l speed of the compressor\, rotational speed of the dynamometer\, power su pplied to the heating element\, and the total mass of air in the system). Along these lines\, different aspects of turbine testing\, turbomachinery map scaling\, component similarity analysis\, as well as simplified analyt ical and numerical turbine heat transfer solutions are discussed. The tool s and considerations associated with this effort will facilitate future en deavors in this research field. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-477@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160720T163000 DTEND;TZID=Asia/Jerusalem:20160720T173000 DTSTAMP:20230603T191503Z URL:https://aerospace.technion.ac.il/events/a-low-cost-laser-range-measure ment-based-terrain-following-concept-and-error-analysis/ SUMMARY:A Low-Cost Laser-Range-Measurement Based Terrain-Following Concept and Error Analysis DESCRIPTION:Lecturer:Arseny Livshitz\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n This seminar addresses the design and error assessment and analysis of a low cost terrain following system for UAVs. Such a syste m enables an aircraft to maintain a pre-defined vertical separation (altit ude) with regard to the terrain surface over which it flies. First papers on this subject date back to the sixties of the previous century\, focusin g primarily on radar based terrain following systems. To address the limit ations and constraints imposed by radar based systems\, new approaches hav e emerged which use electro-optical passive sensors (cameras) and provide better compatibility to the UAV platform.\nIn this study a new approach is proposed to surmount the disadvantages of the previous systems and to pro vide a low cost terrain following solution for UAVs. This system utilizes several laser range sensors in a strap-down configuration as its measureme nt device. The measurements obtained from the sensors are used to generate a desired terrain following trajectory for the aircraft. A trajectory tra cking algorithm is then incorporated to ensure that the aircraft remains o n the desired path\, thus satisfying the required altitude. The complexity and performance of the proposed system depends predominantly on the chose n layout of its sensors as well as the errors of its various components. T he related estimation and control algorithms designed for the terrain foll owing task have to address also system uncertainties and disturbances. The study discusses and thoroughly examines the various error factors affecti ng the system performance. The goal is to develop an analytical error mode l for the system thus pinpointing the different factors which may cause ei ther improvement or degradation in terrain following performance as well a s aid in the design process.\nThe performance of the terrain following sys tem is evaluated using a numerical Monte-Carlo simulation environment cons tructed for this purpose. The simulation results clearly demonstrate that the suggested analytical error model agrees closely with the Monte-Carlo r esults both in trend and in values in the relevant domain. The resulting a nalytical error model quantifies the overall system tracking error\, outli nes the preferred values for various system parameters in order to achieve higher terrain following performance\, and mainly suggests the optimal po inting angle for the laser designators. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-469@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160727T163000 DTEND;TZID=Asia/Jerusalem:20160727T173000 DTSTAMP:20230603T191227Z URL:https://aerospace.technion.ac.il/events/negotiation-between-dynamical- systems-with-connectivity-constraints/ SUMMARY:Negotiation Between Dynamical Systems with Connectivity Constraint s DESCRIPTION:Lecturer:Yaniv Ben Shoushan\n Faculty:Technion Autonomous Syste ms Program\n Institute:Technion – Israel Institute of Technology\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abs tract: \n Details: \n Multi-agent systems (MAS) have been an important are a of study over the past few years. This research will propose a real time sub-optimal solution for an agreement problem in multi-agent systems. Eac h agent is modeled with integrator dynamics and has an associated objectiv e function it wishes to minimizes. Each agent has a preference which it wi shes to reach. The agents must coordinate to reach an agreement on their s tate in finite time. Each agent is able to communicate with other neighbor s according to the connectivity structure. Another constraint considered i n this research is to ensure that each agent will maintain the necessary c ommunication range with its neighbors\, meaning that there will be no dama ge to the connectivity structure that may be caused by a larger distance b etween the agents than the communication radius defined. The main contribu tion of this work is to find a distributed solution to this problem in fin ite-time. This work will propose the distributed algorithm at finite time show and demonstrate a 2-agent case and also will show examples and simula tion results . CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-476@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160803T163000 DTEND;TZID=Asia/Jerusalem:20160803T173000 DTSTAMP:20230603T191447Z URL:https://aerospace.technion.ac.il/events/micro-turbojet-to-turbofan-con version-via-continuously-variable-transmission-thermodynamic-performance-s tudy/ SUMMARY:Micro-Turbojet to Turbofan Conversion via Continuously Variable Tra nsmission: Thermodynamic Performance Study DESCRIPTION:Lecturer:Kobi Kadosh\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In this study\, the viability\, performance\, and character istics of a turbojet-to-turbofan conversion through the use of a continuou sly variable transmission (CVT) are investigated. By an in-house thermodyn amic simulation code\, the performance of the simple cycle turbojet\, a di rect shaft joined turbofan\, and a CVT coupled turbofan with variable bypa ss are contrasted. The baseline turbojet and turbofan findings are validat ed against a commercial software. The comparison indicates high quantitati ve agreement.\nAnalyzing the results of the turbofan engine equipped with a variable bypass and CVT\, it is observed that both the thrust and the ef ficiency are increased. The augmented thrust is observed to be an artifact of enhanced component matching and wider operational range introduced by variable bypass capability. On the other hand\, the introduction of CVT co ntributes to the reduction in fuel consumption. Therefore\, the current re search suggests that adaptation of a micro-turbojet into a variable cycle micro turbofan will greatly improve the performance and efficiency of exis ting engines\, in addition to providing a pathway towards extended use in various applications. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-465@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160817T163000 DTEND;TZID=Asia/Jerusalem:20160817T173000 DTSTAMP:20230603T191058Z URL:https://aerospace.technion.ac.il/events/the-impact-of-reactants-compos ition-on-the-flow-structure-in-wake-stabilized-premixed-flames-mechanism-a nd-scaling/ SUMMARY:The Impact of Reactants Composition on the Flow Structure in Wake S tabilized Premixed Flames\; Mechanism and Scaling DESCRIPTION:Lecturer:Dan Michaels\n Faculty:Reacting Gas Dynamics Lab\, Dep artment of Mechanical Engineering\,\n Institute:Massachusetts Institute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n A major challenge for advanced pr opulsion and combustion technologies is obtaining stable combustion with a wide range of reactant compositions and temperatures. Being able to predi ct the combustion stability\, flow structure and flame location based on a distinctive property of the reactants would be extremely valuable. Recent experimental measurements in two different combustor geometries showed th at both the flow structure and stability map collapse using the flame exti nction strain rate or strained consumption speed. In the present study\, t he origin of those results is investigated using detailed numerical simula tions of wake stabilized laminar lean premixed flames with a wide range of reactants compositions and temperatures. The results reveal the underlyin g feedback mechanism between the flame and the flow field. The analysis sh ows the significant impact of the flame response to stretch on flame stabi lization and associated flow structure. Capturing similar scaling of the c haracteristic chemical and flow time scales in both turbulent and laminar premixed flames indicates that the findings have a fundamental origin. The findings can be extremely useful for other combustors in which the combus tion instabilities originate from the flame-vortex interaction and there i s a need to operate with different fuels and inlet conditions. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-473@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160907T163000 DTEND;TZID=Asia/Jerusalem:20160907T173000 DTSTAMP:20230603T191337Z URL:https://aerospace.technion.ac.il/events/elastic-deformations-control-o f-highly-flexible-aircraft-in-trimmed-flight-and-gust-encounter/ SUMMARY:Elastic Deformations Control of Highly Flexible Aircraft in Trimmed Flight and Gust Encounter DESCRIPTION:Lecturer:Leeran Yagil\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n High-altitude\, long-endurance (HALE) UAVs are characteriz ed by very large aspect ratio wings and low structural weight\, and theref ore are inherently highly flexible. As a result\, these platforms are more susceptible to very large structural deformation in flight and in atmosph eric turbulence. These deformations may severely affect the performance of the aircraft or its function\, as in the case of a wing-embedded antenna. In addition\, analysis of large elastic deformations requires the use of computationally expensive nonlinear models. This work aims to control the large wing deformations that highly flexible aircraft undergo in flight\, by performing trim optimization to constrain wing deformation in steady tr immed flight\, and by minimizing the dynamic response to gust encounter.\n The flexible wing is trimmed and controlled via multiple control surfaces\ , typically located along the leading and trailing edges. Due to the use o f multiple controls\, trimming the aircraft is cast as a trim optimization problem with constraints to find the control surface deflections that tri m the vehicle to a required maneuver while minimizing a specified objectiv e function. In the current study\, the optimization problem is to trim the aircraft to a symmetric maneuver while minimizing the control effort as a n objective\, and constraining wing elastic deformations to a user defined value. Trim optimization is performed using linear programming.\nWhile at trimmed flight\, gust disturbances may result in a large dynamic response . A robust control scheme is designed and applied using H-infinity loop sh aping\, to demonstrate that although the control surfaces are used for tri mming the aircraft\, they have enough authority left to effectively minimi ze elastic wing deformations during gust penetration.\nThe above methodolo gy is demonstrated on a highly flexible flying wing\, similar to the NASA Helios aircraft. It is controlled via two leading- and two trailing-edge c ontrol surfaces. Trim optimization effectively allows trimmed flight at va rious load factors and dynamic pressure values in the flight envelope\, wh ile maintaining small structural deformations\, of about 1/40 of the wing span. The H-infinity controller significantly reduces the maximum wing def lection experienced by a gust disturbance. Thus\, large structural deforma tions can be prevented\, avoiding related performance issues and the need for complex structural geometrically nonlinear analyses for such highly fl exible airframes. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-467@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20160928T163000 DTEND;TZID=Asia/Jerusalem:20160928T173000 DTSTAMP:20230603T191148Z URL:https://aerospace.technion.ac.il/events/belief-space-planning-for-auto nomous-navigation-while-modeling-landmark-identification/ SUMMARY:Belief Space Planning for Autonomous Navigation while Modeling Land mark Identification DESCRIPTION:Lecturer:Shira Har-Nes\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n We investigate the problem of autonomous navigation in un known or uncertain environments\, which is of interest in numerous robotic s applications\, such as navigation in GPS-deprived environments\, mapping and 3D reconstruction\, and target tracking. In lack of sources of absolu te information (e.g. GPS)\, the robot has to infer its own state and to cr eate a model of the environment based on sensor observations\, a problem k nown as simultaneous localization and mapping (SLAM). Moreover\, it has to plan actions\, in order to accomplish given goals while relying on inform ation provided by the inference (estimation) process. The inferred state\, e.g. robot poses and 3D landmarks\, cannot be assumed perfectly known bec ause the observations and dynamics are stochastic\; hence\, planning futur e actions has to take into account different sources of uncertainty. The c orresponding problem is known as belief space planning (BSP).\nAn essentia l ingredient in SLAM and BSP problems is correct association of landmarks observed by robot sensors (e.g. camera)\, as incorrect association might l ead to wrong estimation and to catastrophic results. In particular\, the a bility to re-identify a previously observed object can be challenging\, es pecially considering images taken airborne or on the ground with shallow v iewpoints – an object may look completely different when observed from d ifferent angles. Yet\, state of the art BSP approaches typically consider perfect ability to re-identify an object. In this work we develop a viewpo int aware BSP approach by modeling re-identification aspects within the pl anning phase. We study our approach in simulation\, considering the proble m of autonomously reaching a goal with highest estimation accuracy in a GP S-deprived unknown environment. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-468@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161010T163000 DTEND;TZID=Asia/Jerusalem:20161010T173000 DTSTAMP:20230603T191207Z URL:https://aerospace.technion.ac.il/events/optimal-pursuit-with-rapidly-e xploring-random-trees/ SUMMARY:Optimal Pursuit with Rapidly Exploring Random Trees DESCRIPTION:Lecturer:Vladimir Tchuiev\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n The research addresses the problem of guiding a consta nt speed vehicle to a stationary target while enforcing a terminal heading constraint. A path that minimizes control effort and avoids obstacles sca ttered in the 2D environment is sought. A variation of the rapidly explori ng random tree (RRT) algorithm that is probabilistic complete and is guara nteed to asymptotically converge to the optimal solution is utilized.\nThe talk will begin with an overview on incremental sampling-based RRT algori thms. Then\, the problem at hand will be presented along with the solution approach consisting of two parts: with and without obstacles. The propose d connection methodology between two points sampled by the algorithm\, usi ng a linearization based closed-form guidance solution\, will then be disc ussed. Presentation of methods to reduce computational effort using newly introduced lower bounds for the cost of feasible paths will follow. Analys is of simulation results and some discussion will conclude the talk. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-462@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161102T163000 DTEND;TZID=Asia/Jerusalem:20161102T173000 DTSTAMP:20230603T191007Z URL:https://aerospace.technion.ac.il/events/the-swimming-of-a-slender-fish / SUMMARY:The Swimming of a Slender Fish DESCRIPTION:Lecturer:Ohad Ophir\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n We study hydrodynamic efficiency of a slender fish furnished a with separated caudal fin that swims by flexing its body (say\, left-ri ght). Most fish look and swim that way. Hydrodynamic efficiency of this fi sh obviously depends on the shape of its body and fins and on the way it f lexes\, but it also depends on elastic recoil of its fins (caudal fin in p articular) and dynamic recoil of its body.\nUnder most circumstances\, ela stic recoil of the caudal fin has no detrimental effect on hydrodynamic ef ficiency\; moreover\, in many cases it improves it by placing the fin at a more favorable angle of attack. Because the elastic recoil increases with increasing thrust\, under the same circumstances the efficiency also incr eases with increasing thrust. Indeed some fish prefer moving in short powe rful bursts\, rather than swimming at constant speed. We show that\, under some circumstances\, body recoil can significantly affect hydrodynamic ef ficiency\, leading to cases in which rigid caudal fin is more effective th an the flexible one\, and swimming with low thrust is more effective than swimming with high thrust. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-475@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161109T163000 DTEND;TZID=Asia/Jerusalem:20161109T173000 DTSTAMP:20230603T191411Z URL:https://aerospace.technion.ac.il/events/the-graduated-aeronautical-eng ineer-and-the-aircraft-mro-maintenance-repair-overhaul/ SUMMARY:The Graduated Aeronautical Engineer and the Aircraft MRO (Maintenan ce\, Repair\, Overhaul) DESCRIPTION:Lecturer:Abraham Lavie\n Faculty:Chairman\, Manufacturing Techn ologies Branch\,\n Institute:Mechanical Engineers Society\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The MRO (Maintenance\, Repair\, Overhaul) principles for the Graduated Aeronautical Engineers are essential.\nThe design engineers shou ld consider two issues while performing the design of airborne vehicles: A irworthiness and life cycle cost through the entire operational period. It is important to establish the criteria for inspections required\, life li mited parts and repairs allowed while developing the preliminary concepts of the airborne vehicle\, in order to have positive influence on the total operational cost. The design engineers are responsible for composing the MRO manuals (Parts Manual\, Maintenance/Overhaul Manual\, Repair Procedur es etc.) to meet the Aviation Authorities regulations\, like the CAAI (Civ il Aviation Authority Israel) or FAA (Federal Aviation Authority).\nEngine ers who join operators or MRO facilities should be exposed to the MRO prin ciples to enable them a smooth integration into those organizations. The e ngineers should realize their responsibility and importance to combine bet ween airworthiness need\, readiness and maintenance cost. The maintenance engineers should interpret the manuals' instructions and establish the cor rect ways to execute them. The maintenance engineers are involved in the r epair procedure of expensive parts interfacing with other disciplines as M aterial engineers\, Chemists and Tool Designers. Maintenance engineers sho uld assure that all activities meet Aviation Authorities Regulations.\nIn Israel we have the need for Aeronautical Design Engineers and Maintenance Engineers. Operators xuch as: IAF\, EL-AL\, ISRAIR\, ARKIA\, manufacturers such as: IAI (several groups)\, ELBIT\, AERONAUTICS\, and independent MRO such as: IAI/BEDEK AVIATION GROUP\, TAT REPAIR DEVISION (former Chromallo y). CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-37@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161110T180000 DTEND;TZID=Asia/Jerusalem:20161110T190000 DTSTAMP:20221030T083418Z URL:https://aerospace.technion.ac.il/events/auvsi-project-conclusion-and-p resentation-evening-2016/ SUMMARY:AUVSI Project Conclusion and Presentation Evening 2016 DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Facu lty Auditorium\, room no. 235\n Zoom: \n Abstract: \n Details: The autonom ous airborne system\, designed\, built and flown by a joint team of studen ts from the faculties of Aerospace Engineering and Electrical Engineering\ , will be presented at the event.\n\n\n CATEGORIES:Events LOCATION:Aerospace Faculty Auditorium\, room no. 235 END:VEVENT BEGIN:VEVENT UID:0-459@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161114T163000 DTEND;TZID=Asia/Jerusalem:20161114T173000 DTSTAMP:20230603T190719Z URL:https://aerospace.technion.ac.il/events/task-assignment-and-motion-pla nning-in-the-presence-of-obstacles/ SUMMARY:Task Assignment and Motion Planning in the Presence of Obstacles DESCRIPTION:Lecturer:Yoav Gottlieb\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n In many civil and military missions unmanned vehicles may be expected to cooperate with each other and act as a team. Two main aspe cts of the cooperation are addressed in this research - motion planning an d task assignment\, and the coupling between them. In our problem of inter est Dubins and Reeds-Shepp dynamics are used to model aerial and ground ve hicles’ kinematics\, obstacles are assumed scattered in a 2D environment \, and multiple targets need be serviced possibly with some priority. In t he seminar an approach will first be presented that enables posing in an i ntegrative manner and solving the two aspects associated with this problem of motion planning and task assignment. It is based on using relaxed Dubi ns and Reeds-Shepp paths (that do not enforce a final heading constraint) from each target to the next\, thus making each path independent on the ne xt task. Deterministic and stochastic search algorithms\, for solving the motion planning problem\, will be presented. For solving the task assignme nt problem\, coupled with the motion planning one\, two deterministic\, he uristic and exhaustive\, search algorithms will be presented. The results of sample runs and a Monte-Carlo simulations study will be presented and d iscussed. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-12@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161115T083000 DTEND;TZID=Asia/Jerusalem:20161115T173000 DTSTAMP:20221030T083419Z URL:https://aerospace.technion.ac.il/events/workshop-on-advances-in-micro- gas-turbine-cycle-modeling-and-turbine-hot-section-design-practices/ SUMMARY:Workshop on Advances in Micro Gas Turbine Cycle Modeling and Turbin e Hot Section Design Practices DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Facu lty Auditorium\, Room 235\n Zoom: \n Abstract: \n Details: We will be once again hosting a turbomachinery workshop\,  this time titled " Workshop o n Advances in Micro Gas Turbine Cycle Modeling and Turbine Hot Section Des ign Practices". The two distinguished guest lecturers are Mr. Joachim Kurz ke and Dr. Boris Glezer\, from "MTU Aero Engines / GasTurb" and "Solar Tur bine / Optimized Turbine Solutions" respectively.\nFor the program\, plea se click here.\nThe training activities will be open for all students\, in dustry and academic staff.\n CATEGORIES:Events LOCATION:Aerospace Faculty Auditorium\, Room 235 END:VEVENT BEGIN:VEVENT UID:0-470@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161116T163000 DTEND;TZID=Asia/Jerusalem:20161116T173000 DTSTAMP:20230603T191246Z URL:https://aerospace.technion.ac.il/events/the-timnat-prize-seminar-inves tigation-of-flame-ignition-in-fuel-spray-systems/ SUMMARY:The Timnat Prize Seminar - Investigation of Flame Ignition in Fuel Spray Systems DESCRIPTION:Lecturer:Gershon Kats\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Understanding the spray ignition process is of utmost impo rtance due to the fact that modern combustors in aircraft need to be (re)- ignited under a wide range of (sometimes extreme) operating conditions. Si nce in many of these combustors spark ignition systems are installed\, the amount of spark energy required for successful ignition over a range of o perating conditions must be known. In addition\, the desire to prevent unw anted explosions in transportation and storage of combustibles motivates e xploring the mechanisms at play during the process of ignition. The presen ce of liquid fuel in the form of a multi-sized spray of droplets that must be ignited only serves to increase the difficulty of ignition.\nA new mat hematical analysis is presented of the ignition of a spray/air mixture by an infinite heated surface. In contrast to previous work in the literature the entire history of the ignition process is accounted for starting from the flame embryo progenitor stage\, through the thermal runaway stage to the final flame propagation stage. For tractability at the current stage t he chemical kinetics is taken to be that of a single global reaction. The spray is modeled using the sectional approach and the influence of fuel sp ray characteristics on ignition is determined. Delay in ignition due to th e build-up of vapour from the fuel droplets as well as heat loss to the dr oplets for evaporation are found to play a role. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-47@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161117T080000 DTEND;TZID=Asia/Jerusalem:20161117T090000 DTSTAMP:20221030T083420Z URL:https://aerospace.technion.ac.il/events/the-15th-israeli-symposium-on- jet-engines-gas-turbines/ SUMMARY:The 15th Israeli Symposium on Jet Engines & Gas Turbines DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:\n Zoom: \n Ab stract: \n Details: This year\, as in the previous years\, we plan to hold the Israeli Symposium on Jet Engines and Gas Turbines. During the last fe w years there has seen a considerable expansion of activities in Isreal in turbo jet propulsion. This is in addition to the serial production of sma ll engines\, increased electricty generation using gas turbines and combin ed cycles\, production of various engines' spare parts and maintenance wor k. In Israel\, many bodies are active in jet engines and gas turbine area\ , including: MAFAT (MoD)\, IAF\, Israel Navy\, EL-AL\, IAI\, Beit Shemesh Engines\, RAFAEL\, TAAS\, ORMAT\, Israel Electric Corporation\, R-Jet & \; Becker Engineering\, the Technion and more.\nImproved engineering &\ ; technological innovations and new projects in Israel calls for continued professional meetings\; for the exchange of information\, for cross-polli nation and for creating a fertile seedbed for cooperation. During the prev ious 14 symposia\, in every one\, more than hundred scientists and propuls ion engineers met and presented their work from the various industries\, t he MoD and Academia. These symposia were a success\, wetting the appetite for more such meetings.\nThe 15th symposium is already a mature and establ ished symposium. It will include invited introductory lectures on selected subjects (from large engine manufacturers and Academia). In addition\, th ere will also be presentations that concern activities in different Israel i industrial firms\, institutes and universities as well as an open discus sion and\, upon request\, a tour to the faculty's renovated Turbo and Jet Engine laboratory. This will also be a good opportunity for professional m eetings\, exchange of ideas and presentation of jet engine models and prod ucts from various companies.\nDuring the symposium there will be an opport unity to discuss all topics relevant to jet engines and gas turbines\, inc luding innovative cycles\, aerodynamics of turbo-machines\, combustion\, h eat transfer\, structures and dynamics\, simulations\, control\, productio n processes and maintenance\, combined cycles and more. Preference will be given to subjects of interest in Israel.\nFor the symposium program\, ple ase click here.\nFor more information and the registration form\, please c lick here.\n CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-450@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161123T163000 DTEND;TZID=Asia/Jerusalem:20161123T173000 DTSTAMP:20230603T190353Z URL:https://aerospace.technion.ac.il/events/lowd-highd-hybrid-models-in-wa ve-problems/ SUMMARY:LowD-HighD Hybrid Models in Wave Problems DESCRIPTION:Lecturer:Yoav Ofir\n Faculty:The Interdisciplinary Program for Applied Mathematics\n Institute:Technion – Israel Institute of Technolog y\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoo m: \n Abstract: \n Details: \n The need to reduce the size of large discre te models is a reoccurring theme in computational mechanics in recent year s. One situation which calls for such a reduction is that where the soluti on in some region in a high-dimensional computational domain behaves in a low-dimensional way. Typically\, this situation occurs when the LowD (Low- Dimensional) model is employed as an approximation to the HighD (High-Dime nsional) model in a partial region of the spatial domain. Then\, one has t o couple the two models on the interface between them. Fields of applicati on where the scenario of LowD-HighD coupling is of special interest  incl ude\, among others\, blood-flow analysis\, hydrological and geophysical fl ow models and elastic structures\, where slender members behave in a 1D wa y\, while joints connecting these members possess a 3D behavior. The hybri d HighD-LowD model\, if designed properly\, is much more efficient than th e standard HighD model taken for the entire problem.\nThis work focuses on the coupling of two-dimensional (2D) and one-dimensional (1D) models in t ime-harmonic elasticity. The 2D and 1D structural regions are discretized by using 2D and 1D Finite Element (FE) formulations. Two important issues related to such hybrid 2D-1D models are:  (a) the design of the hybrid mo del and its validation (with respect to the original problem)\, and (b) th e way the 2D-1D coupling is done\, and the coupling error generated. This research focuses on the second issue.\nSeveral methods are adapted to the 2D-1D coupling scenario\, implemented and compared numerically through a s pecially designed benchmark problem \, as well as some more advanced probl ems. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-461@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161128T163000 DTEND;TZID=Asia/Jerusalem:20161128T173000 DTSTAMP:20230603T190756Z URL:https://aerospace.technion.ac.il/events/rd-demonstrations-of-advanced- uas-concepts-present-snapshot-and-future-roadmap/ SUMMARY:R&D Demonstrations of Advanced UAS Concepts - Present Snapshot and Future Roadmap DESCRIPTION:Lecturer:Dr. LTC Ariel Dvorjetski\n Faculty:Head of Concepts an d Unmanned Systems Branch\n Institute:Mafat\n Location:Classroom 165\, gro und floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n I n recent years\, there has been a tremendous growth in the unmanned aerial system market\, for various operational requirements and scenarios.\nMore over\, in nowadays the demands are also derived in from the civil market\, which brings new requirements which were not familiar to the classical mi litary industries.\nAs rapid requirements evolve\, with new “customers ” and new “players”\, the methodology for UAS R&\;D adapts itself to the new market demands.\nThe talk would provide a slight insight to cu rrent R&\;D efforts in the UAS world\, focused in Advanced Propulsion s ystems\, new Aero-Mechanical conceptual designs\,\nand future tactical and multi-rotor UAS Integrated solutions.\nThe discussion would suggest acade mia and industry a distinctive approach for promoting R&\;D activities. \nSuch realm could help creating supporting mechanisms for future joint co llaboration of Academia-Industry-Government programs in the Civil and Mili tary UAS developments. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-448@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161130T163000 DTEND;TZID=Asia/Jerusalem:20161130T173000 DTSTAMP:20230603T190315Z URL:https://aerospace.technion.ac.il/events/full-state-autopilot-guidance- for-multi-input-multi-output-missile-engagements/ SUMMARY:Full-State Autopilot & Guidance for Multi-Input Multi-Output Missi le Engagements DESCRIPTION:Lecturer:Maital Levy\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n There are two main approaches to design autopilot and guida nce systems: “Single-Loop” and “Two-Loop”. In the “Single-Loop ” approach there is no definite autopilot\, and the guidance command is applied directly to the actuators. In the “Two-Loop” approach the inne r autopilot loop has to follow commands generated by the outer guidance lo op\, and each loop is designed separately. The main goal of the research w as to identify the merits of each approach\, and combine the benefits of t he two approaches into a new improved one.\nIn the talk\, the advantages o f the “Two-Loop” and “Single-Loop” approaches will be discussed. T he conditions for obtaining equivalence between the two design approaches will be presented. Broadly speaking\, an equivalence relation between thes e two design approaches holds if full-state feedback exists and the number of guidance commands is equal to the number of available controls. The eq uivalence conditions are established under linear quadratic optimal contro l and differential game formulations\, and for nonlinear systems with boun ded controls. The performance of the “Two-Loop” and “Single-Loop” approaches to design autopilot and guidance systems is illustrated via sim ulations. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-33@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161204T173000 DTEND;TZID=Asia/Jerusalem:20161204T193000 DTSTAMP:20221030T083422Z URL:https://aerospace.technion.ac.il/events/gvahim-excellence-program-cere mony-3/ SUMMARY:“Gvahim” Excellence Program ceremony DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Engi neering Library Classroom (no. 165)\n Zoom: \n Abstract: \n Details: Schol arships and certificates for the students of “Gvahim” excellence progr am\, for the 2015-2016 academic year.\nInvited: The Program's students and their families\, Faculty members\, B.Sc. students and colleagues from the Aerospace Industry .\nFor registration\, please see:\n\n\n CATEGORIES:Events LOCATION:Aerospace Engineering Library Classroom (no. 165) END:VEVENT BEGIN:VEVENT UID:0-452@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20161214T163000 DTEND;TZID=Asia/Jerusalem:20161214T173000 DTSTAMP:20230603T190428Z URL:https://aerospace.technion.ac.il/events/vision-based-dynamic-target-tr ajectory-and-ego-motion-estimation-using-incremental-light-bundle-adjustme nt/ SUMMARY:Vision-based Dynamic Target Trajectory and Ego-motion Estimation Us ing Incremental Light Bundle Adjustment DESCRIPTION:Lecturer:Michael Chojnacki\n Faculty:Technion Autonomous System Program (TASP)\n Institute:Technion – Israel Institute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \ n Abstract: \n Details: \n We investigate autonomous navigation and target tracking in unknown or uncertain environments\, which have become core ca pabilities in numerous robotics applications. In lack of external source o f information (e.g. GPS)\, the robot has to infer its own sate and the tar get's trajectory based on its own sensors observations. For the vision-bas ed case\, the corresponding maximum a posteriori (MAP) estimation is typic ally obtained in a process known as bundle adjustment (BA) in computer vis ion\, or simultaneous localization and mapping (SLAM) in robotics. Both ca ses involve optimization over camera ego-motion (e.g. poses) and all the o bserved 3D features including the dynamic object\, even when the environme nt itself is of little or no interest. Furthermore\, the optimization is p erformed incrementally as new surrounding features are observed\, and thus \, becomes computationally expensive as more data is added to the problem. \nIn this work\, we propose an efficient method for estimating a monocular camera's ego-motion along with dynamic target's trajectory and velocity u sing light bundle adjustment (iLBA). iLBA method allows for ego-motion cal culation using two-view and three-view constraints\, eliminating the need for expensive 3D points reconstruction. Given data association and assumin g no localization signal\, we add to the iLBA optimization framework one s ingle 3D point representing the target each time it is in view. Given a ta rget motion model (e.g. constant velocity)\, we can then calculate the tar get's trajectory and velocity with the camera's ego-motion using graphical models and incremental inference techniques. The target will therefore be the only 3D reconstructed point in the process. We study accuracy and com putational costs by comparing our method to standard BA\, using synthetic and real-imagery datasets collected at the Autonomous Navigation and Perce ption Lab at the Technion. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-463@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170104T163000 DTEND;TZID=Asia/Jerusalem:20170104T173000 DTSTAMP:20230603T191023Z URL:https://aerospace.technion.ac.il/events/membrane-wing-gust-response/ SUMMARY:Membrane Wing Gust Response DESCRIPTION:Lecturer:Sonya Tiomkin\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n During the last decades the use of micro-air vehicles (MA V) in intelligence\, surveillance\, and reconnaissance missions has grown significantly. These missions require the MAVs to present high maneuvering skills while flying at relatively low velocities (around 10 m/s)\, thus m aking their aerodynamic design highly challenging due to the low-Reynolds flow and their sensitivity to atmospheric turbulence (gusts). Low-Reynolds natural flyers with similar dimensions\, such as bats\, often use membran e wings. These are thin\, elastic wings that adapt their shape to the flow conditions. Membrane wings are now implemented in MAVs as well\, with an attempt to mimic nature. The current research focuses on the response of a n elastic membrane wing to unsteady flow conditions\, and in particular to gusts.\nMembrane wings are unique in their ability to deform during fligh t. The membrane shape is determined by an equilibrium of forces between th e aerodynamic load\, the inertial forces\, and the tension along the membr ane. The current research is aimed at studying the membrane wing dynamic r esponse to gusts at low Reynolds numbers. This is obtained by three resear ch phases: first\, the membrane dynamic response to initial conditions is studied analytically for potential flow\, presenting a stability map for t he membrane in terms of the tension and membrane  mass. Then\, the membra ne dynamic response to initial conditions is studied computationally for l ow-Reynolds flow. Finally\, the gust response of a rigid thin airfoil is s tudied in low-Reynolds flow. The combination of these three parts provide insight on the  functionality of membrane wings in gusty environment. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-464@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170109T163000 DTEND;TZID=Asia/Jerusalem:20170109T173000 DTSTAMP:20230603T191039Z URL:https://aerospace.technion.ac.il/events/incorporating-data-association -within-belief-space-planning-for-robust-autonomous-navigation/ SUMMARY:Incorporating Data Association within Belief Space Planning for Rob ust Autonomous Navigation DESCRIPTION:Lecturer:Antony Thomas\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Belief space planning (BSP) and perception are fundamenta l problems in robotics and artificial intelligence\, with applications inc luding autonomous navigation and active SLAM. State-of-the-art BSP approa ches assume that data association (DA)\, i.e. determining the correct corr espondence between the observations and the landmarks\, is given and perf ect. However\, real world environments are often ambiguous\, which in the presence of different sources of uncertainty\, make perception a challeng ing task. For example\, an object might be similar in appearance from the current viewpoint to another object\, while successfully matching images from two different but similar in appearance places (e.g. buildings that l ook alike) would incorrectly indicate the two places as one.  An incorre ct DA can lead to catastrophic results\, e.g. a robot considering it is lo cated in a wrong aliased corridor. Consequently\, more advanced approache s\, known as robust perception\, are required. Yet\, existing robust perce ption approaches focus on the passive case where robot actions are extern ally determined\, while existing BSP methods assume data association to be given and perfect.\n\nIn this research we relax the above assumption and incorporate reasoning regarding DA aspects within BSP\, while accounting f or different sources of uncertainty (imperfect sensing\, stochastic contr ol\, uncertain environment). We develop a data association aware belief sp ace planning (DA-BSP) approach that explicitly reasons about DA within be lief evolution while considering non-myopic planning and multi-modal belie fs represented by Gaussian Mixture Models (GMM). We envision such a frame work to provide robust active perception and active disambiguation capabi lities\, in particular while operating in ambiguous and perceptually alias ed environments. The approach is studied and proven effective using real- world experiments and synthetic simulations\, carried out at the Autonomou s Navigation and Perception Lab at the Technion. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-451@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170111T163000 DTEND;TZID=Asia/Jerusalem:20170111T173000 DTSTAMP:20230603T190413Z URL:https://aerospace.technion.ac.il/events/investigation-of-aluminum-wate r-reaction-for-hydrogen-production-and-energy-storage/ SUMMARY:Investigation of Aluminum-Water Reaction for Hydrogen Production an d Energy Storage DESCRIPTION:Lecturer:Shani Elitzur\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Hydrogen is considered to be the fuel of the future due t o its environmental friendly reaction products\, only water\, and its high specific reaction energy\, about three times more than fossil fuels. The challenges preventing a wide use of hydrogen are associated with its stora ge and transportation problems due to its very low density and high reacti vity and explosion hazard.\nThis research aims at investigating the charac teristics of on-site and on-demand production of hydrogen using the chemic al reaction between aluminum powder and water. It utilizes an original\, p atented\, in-house\, aluminum activation method that enables spontaneous r eaction between aluminum and any type of water at regular conditions\; roo m temperature and atmospheric pressure. The hydrogen produced from the rea ction can be channeled directly into a fuel cell to generate electricity w ithout pollution and at high specific electric energy of up to 2200 Wh/kg Al.\nThe seminar will present an experimental and theoretical investigatio n of the aluminum-water reaction for hydrogen and electric energy producti on on demand for aerospace\, marine\, and ground applications. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-51@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170117T160000 DTEND;TZID=Asia/Jerusalem:20170117T170000 DTSTAMP:20221030T083423Z URL:https://aerospace.technion.ac.il/events/the-launch-of-the-aero-in-the- valley-program/ SUMMARY:The Launch of the “Aero in the valley” Program DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:The WIZO Nahal al Youth Village\n Zoom: \n Abstract: \n Details: The “launch” of the “Aero in the valley” program will take place on January 17\, 2017 the WIZO Nahalal Youth Village.\nThe "Aero in the valley" program will present the world of Aerospace Engineering to students from the prestigious Aniè res Elite Academy program\, which exists in the WIZO Nahalal Youth Village .\nIn the course of the program\, the students will tour in a variety of r elevant industries\, the Israeli Air Force and more\, and will be able to take part in the courses “Introduction to Aerospace Engineering” and “Sports Aviation”\, as provided to students studying at the Technion.\ nFor more information on the Anières Elite Academy program\, click here. \n CATEGORIES:Events LOCATION:The WIZO Nahalal Youth Village END:VEVENT BEGIN:VEVENT UID:0-460@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170118T163000 DTEND;TZID=Asia/Jerusalem:20170118T173000 DTSTAMP:20230603T190736Z URL:https://aerospace.technion.ac.il/events/theoretical-investigation-of-j et-spray-flames/ SUMMARY:Theoretical Investigation of Jet Spray Flames DESCRIPTION:Lecturer:Noam Weinberg\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n In a jet spray flame a jet of liquid fuel spray emerges f rom a small orifice of a burner into a stagnant air environment. The fuel jet entrains air from the surroundings and a mixing layer is formed betwee n the evaporating fuel and the oxygen in the air. Under appropriate operat ing conditions\, a diffusion flame can be established throughout this mixi ng layer. Although jet spray flames are widely used in many engineering ap plications\, such as gas turbines\, jet engines and other energy productio n systems\, a fundamental theoretical understanding of these flames and th eir characteristics has yet to appear in the literature.\nIn the current w ork\, a laminar jet polydisperse spray diffusion flame is nalysed mathemat ically for the first time using an extension of classical similarity solut ions for gaseous jet flames. The analysis enables a comparison to be drawn between conditions for flame stability or flame blow-out for purely gaseo us flames and for spray flames. It is found that\, in contrast to the Schm idt number criteria relevant to gas flames\, droplet size and initial spra y polydispersity play a critical role in determining potential flame scena rios. Some qualitative agreement for lift-off height is found when compari ng predictions of the theory and sparse independent experimental evidence from the literature. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-447@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170123T163000 DTEND;TZID=Asia/Jerusalem:20170123T173000 DTSTAMP:20230603T190256Z URL:https://aerospace.technion.ac.il/events/cooperative-strategies-in-mult i-agent-target-missile-defender-engagement/ SUMMARY:Cooperative Strategies in Multi-Agent Target-Missile-Defender Engag ement DESCRIPTION:Lecturer:Vitaly Shalumov\n Faculty:Technion Autonomous Systems Program (TASP)\n Institute:Technion – Israel Institute of Technology\n L ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n During the course of this research\, a cooperati ve interception scenario between multiple maneuvering targets\, missiles d efending said targets (’defenders’)\, and missiles attacking said targ ets (’missiles’) was investigated.\nThe talk will begin with the intro duction of several computationally efficient Weapon-Target-Allocation (WTA ) algorithms\, developed under the assumption that the target of each miss ile is known\, as well as the guidance law used by each missile and defend er\, and that the number of defenders is equal to that of the missiles. Th e algorithms calculate offline the coefficients contributing to the miss d istance\, using the adjoint representation\, and use those calculations on line.\nA method of tackling a scenario\, where the target is free to decid e at which time to launch the defenders\, will be presented as well. Once WTA is performed\, the multi-agent scenario is decomposed into several one s where in each a specified group of missiles is chasing a specific target \, protected by the assigned defenders.\nThe development of a cooperative target evasion guidance law for said sub-scenario will be presented as wel l.\nA presentation of the simulative evaluation of the cooperative guidanc e law performance\, coupled with the WTA algorithms\, using the notion of Pareto front\, will conclude the talk. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-457@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170130T163000 DTEND;TZID=Asia/Jerusalem:20170130T173000 DTSTAMP:20230603T190640Z URL:https://aerospace.technion.ac.il/events/feasibility-studies-for-early- start-of-a-ramjet-engine-intake-by-flow-bleed/ SUMMARY:Feasibility Studies for Early Start of a Ramjet Engine Intake by Fl ow Bleed DESCRIPTION:Lecturer:Alina Novikov\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n The research deals with the feasibility of an early start of a ramjet air intake using CFD analysis. For this purpose\, a two-dimen sional air inlet geometry with six (6) holes located on the compression su rface (the lower wall of the intake) was chosen. A relatively large amount of mass flow has been sucked through these holes in order to compensate f or the spillage flow\, and obtain an early start. The particular intake ge ometry was designed for a flight Mach number of M=2.7. In order to start t his intake (swallow the ‘normal shock wave’ by acceleration\, the vehi cle had to be accelerated up to M=4.6. Once the intake started\, the vehic le could be decelerated to the design conditions. Only at M=2.6 the norm al shock wave was thrown out\, and the intake turned into an unstarted con dition.\nThe study included CFD simulations at four different flight Mach numbers: 2.4\, 2.6\, 2.8 and 3.0 respectively. The starting condition of e ach simulation was the original geometry of the intake with no open holes. The number of open holes was sequentially increased at each step until al l the six holes were opened. When all six holes were open the intake start ed at all four Mach numbers. However\, when closing the holes one at a tim e\, and returning to the original configuration\, the intake remained star ted for the cases of M=2.8 and M=3.0 but the normal shock was re-expelled to the front of the intake (unstarted intake) for the M=2.6 and M=2.4 cas es. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-458@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170201T163000 DTEND;TZID=Asia/Jerusalem:20170201T173000 DTSTAMP:20230603T190659Z URL:https://aerospace.technion.ac.il/events/towards-a-general-methodology- for-modeling-the-pressure-buildup-behind-porous-media-that-is-impinged-by- a-shock-wave/ SUMMARY:Towards a General Methodology for Modeling the Pressure Buildup beh ind Porous Media that is Impinged by a Shock Wave DESCRIPTION:Lecturer:Omri Ram\n Faculty:Department of Mechanical Engineerin g\n Institute:Ben-Gurion University\n Location:Classroom 165\, ground floo r\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n There are several scenarios where shock waves impinge on porous media. Each of thes e scenarios requires different numerical and experimental approaches to pr edict the intricate shock diffractions and the developing flow fields. As a result\, a universal technique to model them all does not exist. In term s of protective structures\, designers are ultimately required to predict the pressure build up and developing loads behind porous media that are us ed as passive protection to hinder the shock propagation and mitigate the overall load inflicted by it on a structure. Following an experimental stu dy of the parameters affecting the pressure build up in a confined volume behind porous filters impinged by normal shock waves\, a new constitutive model that provided the non-dimensional behavior of the results was derive d (Ram &\; Sadot 2013). A more in-depth analysis of the governing physi cs led to a new understanding of the universality of shock-porous barrier interactions. The results showed that porous barriers placed in the flow f ield acted as low pass filters on the pressure wave. These findings provid ed a physical basis to formulate a new approach that enables studying inte ractions of shock waves and porous barriers. The approach\, addresses ever y porous barrier along with the air confined in it as a single mechanical system. Using this perspective\, a transfer function that links the impose d load at the frontal face of the porous barrier and the developing loads behind it can be found (Ram &\; Sadot 2015). This methodology was appli ed to the case where an explosion-generated blast wave impinged on the fro ntal façade of a structure having a complex inner geometry. A rapid predi ction of the developing loads inside the structure was obtained. This appr oach can replace the need to use a grueling CFD code to simulate the pheno menon (Ram\, Nof &\; Sadot 2016). The methodology was also employed to study the pressure buildup\, following shock impingement\, behind an array of perforated plates. This scenario was poorly understood due to the very complicated shock induced flow field. This method led to a new understand ing of the pressure buildup behind a set of perforated plates including th e influence of different porosities\, different number of plates and diffe rent gasses. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-446@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170213T163000 DTEND;TZID=Asia/Jerusalem:20170213T173000 DTSTAMP:20230603T190238Z URL:https://aerospace.technion.ac.il/events/plasma-assisted-ignition-funda mentals-and-applications-in-subsonic-and-supersonic-flows/ SUMMARY:Plasma-assisted Ignition: Fundamentals and Applications in Subsonic and Supersonic Flows DESCRIPTION:Lecturer:Joseph Lefkowitz\n Faculty:Air Force Research Laborato ry\, Hypersonic Sciences Branch\n Institute:Wright-Patterson Air Force Bas e\, OH\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\ n Zoom: \n Abstract: \n Details: \n The application of novel plasma device s has shown promise for the enhancement of ignition and flame-holding in c ombustion systems. However\, the mechanism by which different discharge ty pes interact with the combustion process is still largely unknown. This wo rk explores the plasma/combustion interaction of nanosecond duration disch arges utilizing both high density localized discharges and low density dif fuse discharges in subsonic and supersonic flows. A variety of optical tec hniques\, including tunable diode laser absorption spectroscopy (TDLAS)\, kilohertz rate OH planar laser induced fluorescence (PLIF)\, optical emiss ion spectroscopy (OES)\, high speed schlieren imaging\, and chemiluminesce nce imaging are used to explore the plasma and combustion processes in sit u. In high density discharges\, it is found that repetitive application of the nanosecond discharges leads to improved ignition probability and flam e-development time at high pulse frequencies (>\;10 kHz)\, indicating so me pulse-to-pulse coupling important for the ignition process. To explore the kinetics involved in this process\, molecular concentration measuremen ts are utilized to track species evolution in the plasma\, and a modeling architecture and kinetic model are developed to shed light on the reaction scheme. It is found that high energy electrons initiate chain propagating or branching reactions which can maintain oxidation at temperatures far b elow the autoignition threshold. In high frequency pulsing\, these kinetic effects result in a positive feedback loop in which radical species are p roduced by both the plasma and combustion reaction processes in series\, l eading to the observed ignition enhancement. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-449@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170215T163000 DTEND;TZID=Asia/Jerusalem:20170215T173000 DTSTAMP:20230603T190334Z URL:https://aerospace.technion.ac.il/events/crlb-for-likelihood-functions- with-parameter-dependent-support-and-a-new-bound/ SUMMARY:CRLB for Likelihood Functions with Parameter-Dependent Support and a New Bound DESCRIPTION:Lecturer:Yaakov Bar-Shalom\n Faculty:\n Institute:University of Connecticut\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In this talk we discuss the regu larity conditions required for the classical Cram´er-Rao lower bound (CR LB) for real-valued (nonrandom unknown) parameters to hold. It is shown t hat the commonly assumed requirement that the support of the likelihood  function (LF) should be independent of the parameter to be estimated can be replaced by the much weaker requirement that the LF is continuous at t he end points of its support.\nParameter-dependent support of the LF arise s when an unknown parameter is observed in the presence of additive measu rement noise and the measurement noise probability density function (pdf) has a finite support. It is also pointed out that the commonly cited re quirements of absolute integrability of the first two derivatives of the L F should be replaced by requirements on the log-LF (LLF). Some practical examples of finite-support measurement noises\, which lead to parameter- dependent LF support\, are discussed in light of the above. For the case where the LF is not continuous at the end points of its support\, a new m odified CRLB — designated as the Cram´er-Rao-Leibniz lower bound (CRLL B)\, since it relies on Leibniz integral rule — is presented and its us e illustrated. The CRLLB is shown to provide valid bounds for a number of  long-standing problems for which the CRLB was shown in the literature a s not valid\, in particular\, for a uniformly distributed measurement noi se. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-453@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170222T163000 DTEND;TZID=Asia/Jerusalem:20170222T173000 DTSTAMP:20230603T190449Z URL:https://aerospace.technion.ac.il/events/spalo-solid-propellant-augment ed-by-a-liquid-oxidizer-from-vision-to-reality/ SUMMARY:SPALO – Solid Propellant Augmented by a Liquid Oxidizer: from vis ion to reality... DESCRIPTION:Lecturer:Yoash Mor\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The SPALO is a new class of solid propellants\, augmented by storable liquid oxidizers. Their structure is similar to conventional soli d propellants\; however\, instead of solid oxidizer particles they contain small liquid oxidizer units. Thus\, the SPALO behaves like a solid propel lant\, but its Isp is higher by 10% and more compared to conventional soli d propellants\, indicating a potential to be the next “big thing” in t he propulsion field.\nThis research aims to promote the SPALO concept towa rds a real propellant. Various chemical and mechanical methods to produce these small liquid oxidizer units have been investigated. We have found a number of ways to lock the liquid oxidizer\, as will be presented.\nA majo r outcome of this research is a novel powerful theoretical formulation and calculation tool – a Modified Thermal Resistance Model (MTRM). The MTRM enables solving relatively easily one-dimensional\, quasi-steady heat tra nsfer problems involving heat sources from chemical reactions or phase tra nsition\, using thermal resistors. Solution of combustion of a liquid drop let and a liquid fuel contained within a porous particle will be demonstra ted. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-26@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170223T090000 DTEND;TZID=Asia/Jerusalem:20170223T100000 DTSTAMP:20221030T083424Z URL:https://aerospace.technion.ac.il/events/open-day-2017/ SUMMARY:"Open Day" 2017 DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:The Technion C ampus\n Zoom: \n Abstract: \n Details: For more details (in Hebrew)\, clic k here.\n CATEGORIES:Events LOCATION:The Technion Campus END:VEVENT BEGIN:VEVENT UID:0-34@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170226T090000 DTEND;TZID=Asia/Jerusalem:20170226T100000 DTSTAMP:20221030T083425Z URL:https://aerospace.technion.ac.il/events/the-third-scientific-conferenc e-for-high-school-students-in-haifa/ SUMMARY:The Third Scientific Conference for High School Students in Haifa DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:The Technion C ampus\n Zoom: \n Abstract: \n Details: This conference will be held at the Technion and will last three days\, during which the students will meet r esearchers from the Technion\, tour in various faculties\, attend lecture s and be exposed to science and engineering demonstrations.\nAs in previou s years\, the students will also tour the faculty of Aerospace Engineering and hear fascinating lectures in the field.\n CATEGORIES:Events LOCATION:The Technion Campus END:VEVENT BEGIN:VEVENT UID:0-455@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170301T163000 DTEND;TZID=Asia/Jerusalem:20170301T173000 DTSTAMP:20230603T190600Z URL:https://aerospace.technion.ac.il/events/fundamental-combustion-study-u sing-counterflow-combustor/ SUMMARY:Fundamental Combustion Study Using Counterflow Combustor DESCRIPTION:Lecturer:Judah Shashank\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n An emerging goal within the aviation industry is to repl ace conventional jet fuel with alternative fuel sources. However\, the com bustion properties of these potential fuels must be thoroughly characteriz ed before they can be considered as replacements in turbomachinery applica tions.  Furthermore\, alternative fuels are developed in order to meet ex isting fuel standards and\, therefore\, will not require modification to e xisting vehicle fleets.\n Opposed jet system is well-suited to evaluate t he similarity of alternative fuels to conventional jet fuel. Design and ma nufacturing of versatile turbulent opposed jet combustor serves as a test bench and can perform tests to evaluate the combustion properties of conve ntional gaseous and liquid jet fuels\, and alternative fuels. This researc h provides a guideline towards performances of different fuels based on ce rtain parameters. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-19@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170302T090000 DTEND;TZID=Asia/Jerusalem:20170302T100000 DTSTAMP:20221030T083426Z URL:https://aerospace.technion.ac.il/events/tech-women-2017-the-2nd-confer ence-for-outstanding-female-high-school-students-from-all-over-israel-will -be-held-at-the-technion-and-the-faculty/ SUMMARY:“Tech Women 2017” - the 2nd conference for outstanding female h igh school students from all over Israel will be held at the Technion and the Faculty DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:The Technion C ampus\n Zoom: \n Abstract: \n Details: For more details (in Hebrew)\, clic k here.\n CATEGORIES:Events LOCATION:The Technion Campus END:VEVENT BEGIN:VEVENT UID:0-456@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170306T163000 DTEND;TZID=Asia/Jerusalem:20170306T173000 DTSTAMP:20230603T190621Z URL:https://aerospace.technion.ac.il/events/rendezvous-guidance-with-appli cation-to-civil-autonomous-aerial-refueling/ SUMMARY:Rendezvous Guidance with Application to Civil Autonomous Aerial Ref ueling DESCRIPTION:Lecturer:Alexander Tsukerman\n Faculty:Technion Autonomous Syst ems Program (TASP)\n Institute:Technion – Israel Institute of Technology \n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom : \n Abstract: \n Details: \n The futuristic concept of civil autonomous a erial refueling using the Boom-Receptacle system\, demands new operational paradigms. Requirements\, such as passenger comfort\, demand that the Tan ker aircraft will approach the Receiver aircraft\, unlike the well-practic ed manual military procedure today. In this paper\, optimal guidance laws are developed and analyzed. The purpose of the guidance law is to steer th e Tanker aircraft from its initial offset relative to the Receiver aircra ft\, until reaching the predefined flight course\, path and separation.\nI nspired by missile intercept problems\, a linear quadratic optimal control problem with terminal intercept angle\, and intercept angular rate constr aints is posed. The goal is achieved by reducing the relative separation a nd aligning the velocity vector of both aircraft at the end of the maneuve r. Two different guidance laws are presented. The first is based on the separated guidance and control design methodology. The guidance portion is derived based on a first-order lag autopilot model. The second is based o n a more detailed model of the Tanker aircraft. The problem is formulated so that the coupling between the relative kinematics and the dynamic model of the Tanker airframe is taken into account\, yielding an integrated gui dance and control architecture. The ability to achieve mid-air rendezvous is demonstrated using numerical simulations and performance is evaluated. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-435@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170306T163000 DTEND;TZID=Asia/Jerusalem:20170306T173000 DTSTAMP:20230530T181048Z URL:https://aerospace.technion.ac.il/events/efficient-belief-space-panning -in-high-dimensional-state-spaces-by-exploiting-sparsity-and-calculation-r e-use/ SUMMARY:Efficient Belief Space Planning in High-Dimensional State Spaces by Exploiting Sparsity and Calculation Re-use DESCRIPTION:Lecturer:Dmitry Kopitkov\n Faculty:Technion Autonomous Systems Program (TASP)\n Institute:Technion – Israel Institute of Technology\n L ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Belief space planning (BSP) is a fundamental pro blem in robotics and artificial intelligence\, with applications including autonomous driving\, sensor deployment and active SLAM. The goal is to au tonomously determine best actions according to a specified objective funct ion\, given the current belief about random variables of interest (e.g. ro bot poses\, tracked target or mapped environment)\, while accounting for d ifferent sources of uncertainty. The objective function typically contains multiple terms\, such as distance to goal\, control cost and a final beli ef uncertainty. The latter measures the amount of information contributed by candidate actions and is the most computationally expensive term to eva luate.\nI present an efficient approach for evaluating the information the oretic term within BSP\, where during belief propagation the state vector can stay fixed in size or be augmented by additional variables (e.g. new r obot poses). Both unfocused and focused problem settings are considered\, whereas uncertainty reduction of the entire system or only of chosen varia bles is of interest\, respectively. State of the art approaches typically propagate the belief state\, for each candidate action\, through calculati on of the posterior information (or covariance) matrix and subsequently co mpute its determinant (required for entropy). In contrast\, our approach r educes run-time complexity by avoiding these calculations. We formulate th e problem in terms of factor graphs and show that belief propagation is no t needed\, requiring instead a one-time calculation that depends on state dimensionality\, and per-candidate calculations that are independent of th e latter. To that end\, we develop an augmented version of the matrix dete rminant lemma\, and show computations can be re-used when evaluating impac t of different candidate actions. These two key ingredients result in a co mputationally efficient (augmented) BSP approach that accounts for differe nt sources of uncertainty and can be used with various sensing modalities. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-443@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170313T163000 DTEND;TZID=Asia/Jerusalem:20170313T173000 DTSTAMP:20230603T190144Z URL:https://aerospace.technion.ac.il/events/flow-control-from-inception-to -application/ SUMMARY:Flow Control: From Inception to Application DESCRIPTION:Lecturer:Michael (Miki) Amitay\n Faculty:Mechanical\, Aerospace and Nuclear Engineering Department\n Institute:Rensselaer Polytechnic Ins titute (RPI)\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Flow control has emerged as an e nabling technology to improve vehicles’ performance.  It involves passi ve and active devices to affect a beneficial change in wall-bounded or fre e-shear flows.  The presentation will provide and demonstrate a few ideas to control flows and the route(s) to application. The talk will be divide d into three major parts:\n\n\n Current and future activities in the Cent er for Flow Physics and Control at RPI.\n Piezoelectric-based actuators\, including synthetic jets\, dynamic low aspect ratio\, surface mounted pin s\, and Piezoelectrically Driven Oscillating Surface (PDOS) actuators and their interaction with different cross flows.  This will include a flow o ver a flat plat\, laminar-turbulent transition control\, and separation co ntrol over flapped airfoils.\n Application: performance enhancement of a vertical tail of a commercial airplane using distributed finite span Synth etic Jet actuators – from small-scale wind tunnel model(s) to flight.\n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-13@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem;VALUE=DATE:20170315 DTEND;TZID=Asia/Jerusalem;VALUE=DATE:20170317 DTSTAMP:20221030T083427Z URL:https://aerospace.technion.ac.il/events/the-57th-israel-annual-confere nce-on-aerospace-sciences-iacas/ SUMMARY:The 57th Israel Annual Conference on Aerospace Sciences (IACAS) DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Dan Panorama T el Aviv Hotel and the Technion campus\n Zoom: \n Abstract: \n Details: The 57th IACAS  will take place on:\nMarch 15\, 2017 – Dan Panorama Hotel \, Tel Aviv\, Israel\nMarch 16\, 2017 – Technion Campus\, Haifa\, Israel \nThe Israel Annual Conference on Aerospace Sciences\, spanning several ge nerations\, is an important annual event on the calendar of the aerospac e community in Israel and arouses a great deal of interest abroad. Taking part in this yearly event are engineers\, scientists and experts in the field of aeronautics and astronautics\, representing well-known local aero space agencies and industries\, as well as participants from major resea rch centers worldwide.\nThe two day conference covers new research\, prese nts up-to-date technology and provides a forum for exchanging new ideas.\n \n CATEGORIES:Events LOCATION:Dan Panorama Tel Aviv Hotel and the Technion campus END:VEVENT BEGIN:VEVENT UID:0-53@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170320T163000 DTEND;TZID=Asia/Jerusalem:20170320T173000 DTSTAMP:20221030T083429Z URL:https://aerospace.technion.ac.il/events/the-4th-annual-professor-singe r-memorial-lecture-the-challenges-in-using-composite-materials-for-aeronau tical-structures/ SUMMARY:The 4th Annual Professor Singer Memorial Lecture - The Challenges i n using Composite Materials for Aeronautical Structures DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Classroom 165\ , ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details:  \;\n\nFor a PDF version of the poster\, click here.\n CATEGORIES:Events LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-454@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170320T163000 DTEND;TZID=Asia/Jerusalem:20170320T173000 DTSTAMP:20230603T190513Z URL:https://aerospace.technion.ac.il/events/the-4th-annual-professor-singe r-memorial-lecture-the-challenges-in-using-composite-materials-for-aeronau tical-structures-2/ SUMMARY:The 4th Annual Professor Singer Memorial Lecture - "The Challenges in using Composite Materials for Aeronautical Structures" DESCRIPTION:Lecturer:Gila Ghilai\n Faculty:Director of Aeronautical Structu res Development\n Institute:Israel Aerospace Industries (IAI)\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n The use of advanced composite structures is continuously increasing in the modern aerospace industry. Military aircraft were the fi rst to take advantage of the weight saving potential of composites. The mo st recent civil aircraft mirror this trend\, with much of their major stru cture exploiting composites. The use of all-composite structures for unman ned vehicles is routine nowadays.\nWhile composites present many advantage s relative to conventional metallic structures\, in terms of weight\, stif fness\, fatigue behavior and corrosion resistance\, they also suffer from many limitations\, especially their labour intensive manufacturing methods \, which result in high recurring cost.\nThe lecture will focus on the cha llenges of implementing composites in aeronautical structures\, and will p resent actual applications in IAI different products\, with the reasoning behind the selection of their structural concept and manufacturing technol ogy. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-437@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170327T163000 DTEND;TZID=Asia/Jerusalem:20170327T173000 DTSTAMP:20230530T181123Z URL:https://aerospace.technion.ac.il/events/visual-engineering-free-hand-t hinking-for-engineers-developers-and-researchers-visual-analysis-and-synth esis-through-sketching/ SUMMARY:Visual Engineering - Free (hand) thinking for engineers\, developer s and researchers - visual analysis and synthesis through sketching DESCRIPTION:Lecturer:Anna Lobovikov-Katz\n Faculty:Senior Lecturer\, Facult y of Architecture and Town Planning\n Institute:Technion – Israel Instit ute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aero space Eng.\n Zoom: \n Abstract: \n Details: \n The ease of use of sophisti cated advanced technologies\, methods and equipment often affects the in-d epth understanding of causes\, rules and principles which underlie the ana lysed processes and phenomena\; e.g.\, for engineers\, the application of computer-generated results without deep understanding of their underlying theoretical and practical bases narrows their professional horizons.\nThis eventually often results in mistakes on a technical level. In the modern computer-aided reality\, highly qualified experts who develop and/or appl y the advanced methods and techniques often complain of such frequent lack of understanding of easily and “automatically” obtained results\, esp ecially among the students and young engineers.\nVisualization has been wi dely known for its uses in STEM (Science\, Technology\, Engineering and Ma thematics)\, and its contribution to learning has been shown in recent re search. Drawing is considered by many researchers as indispensable for vis ual thinking\, while at the same time it contributes to visual skills\, wh ich are the key to success in STEM.\nFreehand sketching is helpful in many diverse areas of STEM\, incl. aeronautical engineering.\nThis ancient tec hnique through its new uses is becoming more and more popular among modern experts\, including the ICT community.\nHowever\, not many possess this s kill\, and who in our rapidly moving reality can afford spending weeks and months to learn sketching?\nThe lecture points out the uses of freehand s ketching and spatial literacy in engineering\, outlines an innovative meth odology which allows for very fast learning of freehand sketching and brie fly exemplifies its application. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-48@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170329T123000 DTEND;TZID=Asia/Jerusalem:20170329T133000 DTSTAMP:20221030T083430Z URL:https://aerospace.technion.ac.il/events/the-facultys-1st-annual-concer t/ SUMMARY:The Faculty’s (1st!) Annual Concert DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty of Aer ospace Engineering\, Auditorium 235\n Zoom: \n Abstract: \n Details: The F aculty’s 1st annual concert will take place on Wednesday\, March 29th\, at 12:30\, in Auditorium 235.\nAll Aerospace Engineering faculty members\, students and employees are most invited to take part -- preferably an act ive one!\nA piano will be available for participants’ use.\nFor details please contact Asst. Prof. Avshalom Manela at amanela@technion.ac.il\n CATEGORIES:Events LOCATION:Faculty of Aerospace Engineering\, Auditorium 235 END:VEVENT BEGIN:VEVENT UID:0-445@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170329T163000 DTEND;TZID=Asia/Jerusalem:20170329T173000 DTSTAMP:20230603T190220Z URL:https://aerospace.technion.ac.il/events/theoretical-study-of-the-3-bra nches-explosion-limits-of-a-flammable-system/ SUMMARY:Theoretical Study of the 3-branches Explosion Limits of a Flammable System DESCRIPTION:Lecturer:Alon Lidor\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n The phenomenon of explosion (or self-ignition\, not to be co nfused with detonation) of fuel mixtures is well known\, both as a desired phenomenon\, such as the ignition of the fuel in Diesel engines\, and as a phenomenon to be avoided\, like knocking in SI engines or the risk of fi res on oil and gas platforms. The explosion limits are defined as the curv e on a pressure-temperature diagram which describes the threshold between the explosive and non-explosive regions of a fuel mixture. These limits ar e uniquely defined for a specific fuel-oxidizer pair\, under a specific ra tio and are also partially dependent on the vessel wall surface. For hydro gen and many hydrocarbon fuels distinctive 3-branched limits exist. Althou gh the explosion limits have been studied extensively (experimentally and theoretically) for many years\, there exists no model to date which can ac curately predict the explosion limits over the complete range\, capturing this unique branching behavior.\nThis research is composed of theoretical investigation of the explosion limits of an H2-O2 mixture\, with the objec tive of understanding fundamental governing physics of the explosion limit s\, especially in regards to the uniqueness of the branching limits. We al so aim to develop a universal explosion criterion for H2-O2 mixtures\, and gain insights into the explosion process for other fuel types. By using a novel approach\, combining elements of chain ignition theory and linking between the explosion limits and the ignition delay\, we present a unified model capable of accurately predicting the explosion limits of H2-O2 mixt ure. We also investigate the effects of fluctuations at the molecular leve l\, to evaluate the effect of different impurities in the mixture on the e xplosion initiation. Our results from the different models developed and t he conclusions and insights gained about the explosion phenomenon will be presented in the talk. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-39@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170419T123000 DTEND;TZID=Asia/Jerusalem:20170419T143000 DTSTAMP:20221030T083431Z URL:https://aerospace.technion.ac.il/events/the-2017-annual-faculty-gradua te-studies-research-day/ SUMMARY:The 2017 Annual Faculty Graduate Studies Research Day DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:The Faculty Lo bby\n Zoom: \n Abstract: \n Details: The 2017 Annual Faculty Graduate Stud ies Research Day will take place on Wednesday\, April 19\, 2017 between 12 :30 and 14:30.\nGraduate students will present their research in poster fo rmat to an audience\, including Faculty members\, guests from industry and other Faculties\, graduate and undergraduate students.\nFollowing common practice at many conferences\, a pre-poster session will be held first in Room 165\, during which graduate students will briefly present the topics of their research.\nThe posters themselves will be exhibited by the gradua te students in the Faculty lobby\, on both 1st and 2nd floors.\nAt the end of the event\, prizes in two categories will be awarded. The best posters will be chosen after evaluation by a committee (comprised of Faculty memb ers). The most popular poster will be chosen by the audience in a secret b allot.\n CATEGORIES:Events LOCATION:The Faculty Lobby END:VEVENT BEGIN:VEVENT UID:0-442@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170419T163000 DTEND;TZID=Asia/Jerusalem:20170419T173000 DTSTAMP:20230603T190122Z URL:https://aerospace.technion.ac.il/events/cooperative-strategies-and-cap ture-zones-in-multi-plater-pursuit-evasion-games-2/ SUMMARY:Cooperative Strategies and Capture Zones in Multi-Player Pursuit-Ev asion Games DESCRIPTION:Lecturer:Shmuel Hayoun\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Cooperative strategies are becoming more and more popular with the continuing evolution and advancement in decision making capabili ties of autonomous vehicles. Utilizing multiple agents to perform a given task can be beneficial even in cases when the goal is achievable by a sing le agent. With regard to interception engagements of an intelligent target \, through shared information and coordinated actions the capability requi rements and/or the number of required agents in order to capture the targe t may be relaxed and reduced\, respectively. It is therefore a great point of interest\, when analyzing such problems\, to discern under what condit ions the evader's capture can be guaranteed (and whether or not these cond itions are dependent on the number of pursuers and their capabilities) and which element of cooperation (if any) can help to achieve this guarantee. \nWe will begin the talk with an examination of the solution of a linear 1 -on-1 interception engagement with multiple bounded control inputs\, formu lated as a two-person\, zero-sum\, pursuit-evasion game\, from which we de rive the conditions under which a single pursuer may guarantee the exact c apture of a single (possibly) evading target\, extending current known res ults. This will be followed by an analysis of a 2-on-1 pursuit-evasion gam e (a team of two pursuers vs. a single evader) in which we consider two di fferent formulations: the first including a product-form cost function and the second using a guaranteed miss approach. Based on the latter\, we wil l propose a cooperative pursuit strategy for a couple of “weak” pursue rs and illustrate its performance through simulations. Finally\, following some observations from the 2-on-1 game\, we will present necessary and su fficient conditions by which a group of (possibly) cooperating pursuers ma y guarantee point capture of a single (possibly) evading target in a gener al n-on-1 linear engagement\, showing that\, with respect to guaranteeing point capture\, the pursuers cannot actually benefit from cooperating with one another. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-441@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170423T113000 DTEND;TZID=Asia/Jerusalem:20170423T123000 DTSTAMP:20230603T190102Z URL:https://aerospace.technion.ac.il/events/cavitational-flows-the-geometr y-of-a-supercavitation-bubble/ SUMMARY:Cavitational Flows / the Geometry of a Supercavitation Bubble DESCRIPTION:Lecturer:Lotan Ludar\n Faculty:Department of Mathematics\n Inst itute:Technion – Israel Institute of Technology\n Location:Meeting Hall 203\, 2nd floor\, Fine Rocket Propulsion Center\, Aerospace Engineering\n Zoom: \n Abstract: \n Details: \n Cavitation\, i.e. the appearance of vap or cavities inside an initially homogeneous liquid medium\, occurs in diff erent situations commonly characterized by the pressure decrease below the vapor pressure of the liquid. The vapor structures are often unstable\, a nd when reaching a zone of increased pressure\, they may violently collaps e. Thus\, at a first glance\, cavitation appears as a harmful phenomenon t hat should be avoided. The Russians were the first to identify a positive implication of cavitation\, called supercavitation\, and built a torpedo b ased on this technology. As the cavitation parameter decreases\, a small c avity attached to an underwater body will extend and grow longer and longe r\, enveloping the entire body. Its overall drag with the surrounding will decrease significantly. Understanding the geometry of a supercavitation b ubble is essential to the design of supercavitational underwater vehicles and applications. In a series of experiments we have investigated the deve lopment and shape of supercavitation bubbles under various operating condi tions and different cavitators. Using a new theoretical approach we have e xamined the bubble shape and its stability for different geometries and di sturbances. The research brings new insight for the phenomena of supercavi tation bubbles. CATEGORIES:Seminars LOCATION:Meeting Hall 203\, 2nd floor\, Fine Rocket Propulsion Center\, Ae rospace Engineering END:VEVENT BEGIN:VEVENT UID:0-439@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170426T163000 DTEND;TZID=Asia/Jerusalem:20170426T173000 DTSTAMP:20230530T181200Z URL:https://aerospace.technion.ac.il/events/reduced-system-order-and-sensi ngactuation-resolution-for-estimation-and-control-of-transition-to-turbule nce-2/ SUMMARY:Reduced System Order and Sensing/Actuation Resolution for Estimati on and Control of Transition to Turbulence DESCRIPTION:Lecturer:Aaron Friedman\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Skin drag in shear flows can be significantly reduced by maintaining laminar versus turbulent flow\, rendering the control or dela y of transition to turbulence of engineering interest. Controlling transit ion from laminar to turbulent plane Poiseuille flow serves as a model prob lem for more geometrically complex or realistic shear flows\, such as boun dary layers or pipe flow. In previous numerical studies\, application of a linear systems approach to controlling transition to turbulence in plane Poiseuille flow has been shown to increase transition thresholds by at lea st several factors\, depending on the type of flow perturbation assumed. G enerally speaking\, these studies have two primary shortcomings: large mod el order and assuming a continuum\, or near continuum\, of wall-mounted se nsors and actuators.\n\nThis research attempts to address the aforemention ed shortcomings and progress toward physically realizable actuation and se nsing. Performance is measured by searching for controlled and uncontrolle d transition thresholds in a pseudo-spectral direct numerical simulation ( DNS) of the Navier-Stokes equations written in-house. Firstly\, our resear ch examines the degree to which peak transition threshold improvement can still be obtained both by controlling only a narrow range of wave-number p airs and by using sparsely distributed discrete actuators under the assump tion of full-state feedback. Secondly\, we investigate the use of sparsely distributed discrete sensors\, which relies upon the assumption that only a narrow range of wave-number pairs is of interest for state estimation a nd control\, and apply a heretofore unused technique for filtering the eff ects of sensor spillover caused by deliberate undersampling: state-augment ation. Finally\, the use of sparsely distributed actuators and sensors tog ether is tested against spatially continuous actuation and sensing\, demon strating the transition threshold performance recovery ability of state-au gmentation for filtering spillover effects. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-436@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170503T163000 DTEND;TZID=Asia/Jerusalem:20170503T173000 DTSTAMP:20230530T181104Z URL:https://aerospace.technion.ac.il/events/thrust-inclination-guidance-an d-control/ SUMMARY:Thrust Inclination Guidance and Control DESCRIPTION:Lecturer:Prof. Shaul Gutman\n Faculty:Department of Mechanical Engineering\n Institute:Technion – Israel Institute of Technology\n Loca tion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Ab stract: \n Details: \n In exo-atmospheric guidance the control is the thru st vector. A recent thrust vector approach has revealed that in optimal gu idance the thrust inclination in an inertial frame is constant. Thus\, in this talk\, the usual acceleration vector command is replaced by the thrus t inclination scalar command. An autopilot that keeps the thrust inclinati on constant completes the guidance loop. The guidance law is based on the range\, Line-Of-Sight (LOS) angle\, and their derivatives. This is done wi thout kinematics linearization. Simulations demonstrate the overall perfor mances. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-15@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170515T140000 DTEND;TZID=Asia/Jerusalem:20170515T200000 DTSTAMP:20221030T083432Z URL:https://aerospace.technion.ac.il/events/technion-undergraduate-student s-recruitment-day-in-tel-aviv/ SUMMARY:Technion Undergraduate Students Recruitment Day in Tel Aviv DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Azrieli Center \, Tel Aviv\, Round Building\, 49th Floor\n Zoom: \n Abstract: \n Details: The Technion is coming to Tel Aviv and you have another opportunity to ap ply for undergraduate studies.\n\nFor more details (in Hebrew)\, including the schedule of the lectures\, and to register for the event\, please cli ck here.\n\n \;\n CATEGORIES:Events LOCATION:Azrieli Center\, Tel Aviv\, Round Building\, 49th Floor END:VEVENT BEGIN:VEVENT UID:0-444@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170517T163000 DTEND;TZID=Asia/Jerusalem:20170517T173000 DTSTAMP:20230603T190200Z URL:https://aerospace.technion.ac.il/events/new-propellants-for-ion-thrust ers-iodine-and-other-alternatives/ SUMMARY:New Propellants for Ion Thrusters – Iodine and Other Alternatives DESCRIPTION:Lecturer:Dr. Kristof Holste\n Faculty:Institute of Experimental Physics I\n Institute:Justus-Liebig-University of Giessen\, Germany\n Loc ation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n A bstract: \n Details: \n Ion thrusters are nowadays routinely used on satel lites for attitude control and for dedicated space missions\, such as GOCE and Dawn. The commonly used propellant for ion thrusters is the noble-gas xenon\, which comprise some advantages such as high atomic mass\, no chem ical reactivity\, and efficient ionization. One disadvantage of xenon is t he high price\, which leads to high costs for testing and qualification of thrusters. Potential candidates for alternative propellants are currently under investigation in the electric propulsion community. An interesting material is iodine\, which has a high mass\, a high ionization efficiency and a high density due to its solid nature at standard temperature. It can be evaporated with moderate heating power and was successfully tested rec ently at Giessen university with a radiofrequency ion thruster. The talk w ill present performance results of iodine and gives an overview about alte rnative propellants in general. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-425@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170522T163000 DTEND;TZID=Asia/Jerusalem:20170522T173000 DTSTAMP:20230530T180747Z URL:https://aerospace.technion.ac.il/events/parametric-investigation-of-al uminum-tungsten-and-fluor-polymer-mixtures/ SUMMARY:Parametric Investigation of Aluminum\, Tungsten and Fluor-Polymer M ixtures DESCRIPTION:Lecturer:Hila Shaltieli\n Faculty:The Interdisciplinary Program of Design and Manufacturing Management\, Faculty of Aerospace Engineering \,\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n The Reactive materials under study are solids mixtures of Al uminum\, Tungsten and different types of Fluor-Polymer powders. The metal powders used as the fuel and the Fluor- Polymers as oxidizers of the mixtu res. The Energy release potential of Aluminum / Fluor- Polymer mixture is very significant. Indeed\, under certain conditions\, provided that the po lymer chain starts to brake\, an exothermic reaction between the reactants produces a great amount of heat\, gases and solid particles residues. The main issues in the lecture will be the ignition characteristics as well a s thermal and output performance of the mixtures. In order to examine thes e parameters\, different types of mixtures were prepared and a variety of measurements and comparative experiments were conducted. The research incl uded thermal and calorimetric analyses performed in three different instru ments\, and different experiments to examine the ignition reaction\, among them open burning and closed vessel experiments. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-434@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170604T163000 DTEND;TZID=Asia/Jerusalem:20170604T173000 DTSTAMP:20230530T181030Z URL:https://aerospace.technion.ac.il/events/about-new-approaches-in-the-st udy-of-the-initiation-reactivity-of-nitramines/ SUMMARY:About New Approaches in the Study of the Initiation Reactivity of N itramines DESCRIPTION:Lecturer:Prof. Svatopluk ZEMAN\n Faculty:Institute of Energetic Materials\, Faculty of Chemical Technology\n Institute:University of Pard ubice\, The Czech Republic\n Location:Meeting Hall 203\, 2nd floor\, Fine Rocket Propulsion Center\, Aerospace Engineering\n Zoom: \n Abstract: \n D etails: \n Extemporary short intermolecular distances of nitro groups in t he crystal lattice of polyniro compounds led towards invocation of activit ies in the research of free spaces (free volumes\, DV) in crystals of EMs and of their influence on impact sensitivity of the mentioned energetic co mpounds. The first published papers from this area have awoke our interest also in verification of the mentioned influence not only on impact\, fric tion and electric spark sensitivities\, and thermal reactivity\, but also on crystal densities and performance\, which is demonstrated on 24 nitrami nes.\nThe relationships between sensitivity and the crystal lattice free s pace per molecule\, DV\, in the nitramine crystals are described by equati ons which are divided into a number of sub-relationships\, each of them wi th a strong limitation by the molecular-structural characteristics of such compounds. With exception of the impact sensitivity\, increasing DV value s leads mostly to decreasing of initiation reactivity of the nitramines st udied. In the case of impact sensitivity it is not possible to say uniquel y that increasing of the DV values leads to its increasing or decreasing\; this is differet from published opinion. Several little exceptions from t he mentioned trends have analogies in other relationships of sensitivity\, for example “spark energies - bond dissociation energies” or in the c ase of impact sensitivity in relation “impact sensitivity – volume hea t of explosion”.\nMore detailed analysis of a mutual dependence of volum e heat of explosion\, rQ\, on the crystal lattice free volume\, DV\, shows that their courses are relatively tight but they are not unequivocal. Par tial linear relationships for the rQ values mostly show increase of this c haracteristic with increasing the DV values\, but here also some opposite trends exist.  A similar situation is in semilogarithmic relationship bet ween the crystal density\, r (important characteristics for detonation and performance)\, and the DV values of the nitramines studied\; here the stu died substances are as if divided into a group derived from dimethyl nitra mine and a group derived from 2\,4\,6\,8\,10\,12-hexanitro-2\,4\,6\,8\,10\ ,12-hexaazaisowurtzitane (HNIW). All the analyzed dependencies confirm tha t in the non-ionic nitramines maximal density and detonation parameters ar e limited by values which are peculiar to e-HNIW.\nThe found relationships for the impact and friction sensitivities confirm the disorder in distrib ution of the forces in the crystal lattice of the “common” quality of  e-2\,4\,6\,8\,10\,12-hexanitro-2\,4\,6\,8\,10\,12-hexaaza-isowurtzitane (CL-20)\, in comparison with its RS (reduced sensitivity) or chemically pu re analogue\; these relationships allow also to speculate\, which of the n itro groups in the CL-20 molecule might have a main participation in the i ntermolecular interactions for its particular kind. CATEGORIES:Seminars LOCATION:Meeting Hall 203\, 2nd floor\, Fine Rocket Propulsion Center\, Aer ospace Engineering END:VEVENT BEGIN:VEVENT UID:0-438@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170605T163000 DTEND;TZID=Asia/Jerusalem:20170605T173000 DTSTAMP:20230530T181144Z URL:https://aerospace.technion.ac.il/events/cfdquasi-steady-coupled-trim-a nalysis-of-diptera-type-flapping-wing-mav-in-steady-flight/ SUMMARY:CFD/Quasi-Steady Coupled Trim Analysis of Diptera-type Flapping Win g MAV in Steady Flight DESCRIPTION:Lecturer:Dr. Camli Badrya\n Faculty:Aerospace Engineering Depar tment\n Institute:University of Maryland\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The aerodynamic phenomena that keep insect aloft are drastically different fro m that of a fixed-wing or rotary-wing based aircraft. While there is a goo d level of understanding of the principles behind insect flight\, the nuan ces in the aerodynamics are not yet fully understood to the extent where c oncepts can be translated to practical designs. Insects utilize large unst eady aerodynamic forces to hover in gusty conditions\, fly forward\, sidew ays and even perch upside down. The nature of the flow they operate in is highly viscous\, which leads to vortex formation and flow separation that is inherently unsteady. High-fidelity simulations can provide precise inst antaneous airloads at these length scales\, especially where performing ex periments can be challenging. Consequently\, computational tools can be us ed to accurately model the unsteady flowfield around flapping wings.\nFrom an engineering perspective\, it is useful to compare the performance of d ifferent flapping wing configurations (in steady forward flight or coordin ated turn) under ``trimmed'' flight conditions. Without an efficient trim algorithm\, trial-and-error based identification of the trimmed wing kinem atics is computationally expensive for any flight condition\, because the large number of simulations required makes the process practically infeasi ble. In a global sense the nature of forces produced by flapping wings clo sely resemble those on a helicopter blade\, such that an analogy can be dr awn between the two. Therefore\, techniques developed for helicopter perfo rmance calculation are adapted and applied to the flapping wing platform p articularly for analyzing steady flight. The aim of this study is\, theref ore\, to formulate a computationally efficient and robust framework to obt ain trim solutions that couples a flight dynamic model using simplified qu asi-steady (QS) wing aerodynamics to a high-fidelity CFD analysis. Such an analysis will provide the ability to incorporate the effects of detailed aerodynamic forces from CFD into the trim solution for flapping wing kinem atics for the first time.\nThe coupling process resulted in key insights\, both on the numerical and physics fronts. First\, it was shown that the c oupled trim methodology based on the QS model is capable of driving the CF D towards a stable trim solution. And in doing so\, the CFD/QS coupled str ategy is much cheaper and faster than an isolated CFD approach\, while mai ntaining the accuracy of the trimmed solution. In steady flight it was obs erved that the airloads\, thrust and power are affected by the trim parame ters\, and the CFD/QS methodology accurately accounted for these inter-dep endencies. The lift-to-power ratio versus average lift was identified as a principal efficiency metric to assess the performance of flapping-wing ve hicles for a given geometry and kinematic parameters. All of the relevant nonlinear aerodynamic interactions between the wing and its surrounding en vironment were first verified experimentally in hover and then explored fu rther in level forward flight and a coordinated turn. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-432@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170607T163000 DTEND;TZID=Asia/Jerusalem:20170607T173000 DTSTAMP:20230530T180956Z URL:https://aerospace.technion.ac.il/events/propulsion-system-for-autonomo us-vessels-using-oscillating-foils/ SUMMARY:Propulsion System for Autonomous Vessels Using Oscillating Foils DESCRIPTION:Lecturer:Guy Kagan\n Faculty:Technion Autonomous Systems Progra m (TASP)\,\n Institute:Technion – Israel Institute of Technology\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abs tract: \n Details: \n A novel bio-inspired propulsion system for autonomou s vessels is suggested using two vertical oscillating hydrofoils in a side -by-side configuration. This research examines the feasibility of such a s ystem for enabling high maneuverability as well as better efficiency using the relative movement between the two foils compared to a propulsion syst em based on a single oscillating foil. The motivation for using oscillatin g foils in autonomous vessels are the need to save energy for long range m ission by creating a more efficient propulsion system and the ability to c ombine the thrust unit and the maneuvering unit into one system\, making t he vessel easier to control. This system will enable autonomous control of the vessels by changing speed and phase of the hydrofoils to provide both thrust and maneuverability with one unit.\nAn overview will be given of t he movements of natural swimmers\, followed by the explanation of the kine matics and the forces acting on a foil undergoing heaving and pitching mot ions. The purpose of the experimental system and the specifications will b e defined. From these\, various design configurations of the system will b e presented\, which will emphasize the mechanics\, the array of sensors\, electronics\, software and more. The selected configuration will be presen ted in detail as well as the calibration methods and feasibility testing a gainst previous experiments. A number of experimental results will then be presented.  The presentation will end with recommendations for improving the system as well as additional work that can be performed on the subjec t in the future. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-433@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170614T163000 DTEND;TZID=Asia/Jerusalem:20170614T173000 DTSTAMP:20230530T181013Z URL:https://aerospace.technion.ac.il/events/an-investigation-of-water-in-f uel-emulsion-spray-combustion/ SUMMARY:An Investigation of Water-in-Fuel Emulsion Spray Combustion DESCRIPTION:Lecturer:Neta Yokev\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Of the many ideas being considered to attempt to meet the st rict standards dictated by protocols to reduce harmful NOx and PM emission s to the atmosphere is the use of water-in-fuel emulsions (WIFE). The curr ent research addresses the combustion of a spray of droplets that are comp rised of two immiscible fluids components viz. water and fuel\, with the w ater being contained within an outer liquid shell of fuel. The fuel and wa ter evaporate sequentially. By strategically placing the fluid with higher volatility and latent heat of vaporization at the core a phenomenon calle d micro-explosion may be induced (under appropriate operating conditions)\ , in which smaller fuel droplets are produced. Two main benefits accrue to the process of combustion by using WIFE sprays: (a) a reduction in the co mbustion temperature\, thereby reducing harmful emissions\, and (b) an inc rease in fuel efficiency\, by creating a second mechanism of atomization.\ nA model is presented for a one-dimensional laminar premixed flame\, propa gating into a rich\, off-stoichiometric\, fresh homogenous mixture of wate r-in-fuel emulsion spray\, with air and inert gas. The two main purposes o f this thesis is to investigate the effect of initial water content and to tal liquid droplet loading on the (a) steady-state velocity of the propaga ting flame and burnt temperature\, and (b) the cellular and pulsating stab ility limits of such flames. The influence of the micro-explosion of the s pray’s droplets on the flame’s characteristics will be highlighted for the first time. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-426@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170625T163000 DTEND;TZID=Asia/Jerusalem:20170625T173000 DTSTAMP:20230530T180806Z URL:https://aerospace.technion.ac.il/events/4d-printing-making-3d-printing -alive/ SUMMARY:4D Printing: Making 3D Printing Alive DESCRIPTION:Lecturer:Prof. H. Jerry Qi\n Faculty:The George W. Woodruff Sch ool of Mechanical Engineering\n Institute:Georgia Institute of Technology\ , Atlanta\, Georgia\, USA\n Location:Classroom 165\, ground floor\, Librar y\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n 4D printing is a no vel concept that emerges in recent years\, benefiting from the rapid devel opment of advanced 3D printing technologies and active materials. In 4D pr inting\, upon external stimuli on demand\, a 3D printed part can change it s shapes as a function of time\, which becomes the 4th dimension of the sh ape forming process. 4D printing offers the advantages of forming complica ted 3D shapes from low dimensional structures\, saving printing materials and printing times\, etc. These make it suitable for applications includin g morphing structures\, sensors\, actuators\, and soft robots.\nIn this ta lk\, we start with the concept of 4D printing. We then introduce several d ifferent approaches to achieve 4D printing\, including using hydrogel base d 3D printing method where the hydrogel swelling behavior is coupled with structure anisotropy\, printed active composites that utilize multimateria l 3D printing\, and internal stress based approach where the residual stre ss generated in 3D printing process is used to promote shape change. Final ly\, we discuss the challenge and future directions for 4D printing. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-423@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170626T163000 DTEND;TZID=Asia/Jerusalem:20170626T173000 DTSTAMP:20230530T180700Z URL:https://aerospace.technion.ac.il/events/the-flow-generated-by-an-oscil lating-plate/ SUMMARY:The Flow Generated by an Oscillating Plate DESCRIPTION:Lecturer:Gregory Khodos\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n We study the flow generated by the periodic pitching mot ion of a 2D rigid plate about its fixed end in an unbounded incompressible fluid which is otherwise at rest\, as a simple model of the operation of micro fans. The problem\, which is inherently non-linear even for small-am plitude oscillations\, is addressed within the framework of a semi-analyti c model of inviscid flow incorporating concentrated vortex shedding at the free end. This semi-analytic model successfully predicts the longitudinal impulse imparted to the fluid in agreement with NS (FLUENT) simulations p roviding insight into the physical mechanisms underlying the primary contr ibutions to the impulse. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-427@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170628T163000 DTEND;TZID=Asia/Jerusalem:20170628T173000 DTSTAMP:20230530T180824Z URL:https://aerospace.technion.ac.il/events/disturbance-source-identificat ion-for-flow-control/ SUMMARY:Disturbance Source Identification for Flow Control DESCRIPTION:Lecturer:Igal Gluzman\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n We present a novel approach for identifying disturbance so urces in wall-bounded shear flows\, which can prove useful for active cont rol of boundary layer transition from laminar to turbulent flow. The idea underlying this research is to consider the flow state\, as measured in se nsors\, as a mixture of sources\, and to use Blind Source Separation (BSS) techniques to recover the separate sources and their unknown mixing proce ss.\nWe begin by introducing a BSS method based on the Independent Compone nt Analysis (ICA) technique\, and provide physics-based criteria for prope r sensor placement in order to successfully separate Tollman-Schlichting ( TS) wave disturbances. We verify these criteria by successfully implementi ng the ICA method in appropriate computer simulations of shear flow.\nTo a lleviate the limitations of the ICA-based source identification technique\ , we next present a BSS method based on the Degenerate Unmixing Estimation Technique (DUET). This method can be used to identify any (a priori unkno wn) number of sources by using the data acquired by only two sensors.  We adapt and apply the DUET method to identify disturbance sources in measur ed mixtures comprising TS waves and wave-packets. Furthermore\, we extend the DUET-based method to also determine the propagation velocity vector of each of the identified sources by using sensor signals from three differe nt locations in the flow field.  The viability of the method is demonstra ted via numerical simulations and specially-designed wind-tunnel experimen ts.\nThe BSS-based identification methods presented in this work rely on t he capability to accurately measure velocity signal mixtures using nonline ar flow sensors\, such as hot-wire flow velocity probes. This gives rise t o the problem of fast and accurate sensor calibration. To address this iss ue we have developed a Gaussianization-based statistical calibration techn ique for estimating the nonlinear calibration curve of hot-wire probes.  The method uses as input a measured sequence of voltage samples\, correspo nding to different unknown flow velocities in the desired  operational ra nge\, and only two measured voltages along with their known (calibrated) f low velocities. The novel calibration method is validated against standard calibration methods using data acquired by hot-wire probes in wind-tunnel experiments. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-424@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170703T163000 DTEND;TZID=Asia/Jerusalem:20170703T173000 DTSTAMP:20230530T180726Z URL:https://aerospace.technion.ac.il/events/a-prescriptive-model-of-the-co nceptual-engineering-design-process-based-on-parameter-analysis-and-c-k-th eory/ SUMMARY:A Prescriptive Model of the Conceptual Engineering Design Process B ased on Parameter Analysis and C-K Theory DESCRIPTION:Lecturer:Gil Weisbrod\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The importance of the conceptual design stage within the p rocess of engineering design of a new product is well known. This stage is considered the most important in terms of its effect on the success of th e final product. A better understanding of the conceptual design stage\, a chieved through research\, will lead to products with better quality and v alue and shorter time to market.\nThe objective of the current research wa s to develop a new prescriptive model for the conceptual engineering desig n stage\, based on the theoretical foundation of C-K Theory and the empiri cally-derived conceptual design method called Parameter Analysis (PA). The proposed model is intended to combine the benefits of C-K Theory and PA\, as well as overcome the lack of a strong theoretical foundation in PA and the insufficient prescriptive power of C-K Theory. The development proces s of the new model was similar to product development. It started with con ceptualization in order to define a set of key factors and principles\, i. e.\, the conceptual foundation or the “ideology” of the new prescripti ve model. Next\, those principles were integrated into a structured system atic procedure to form the new model\, called ICE (Idea-Configuration-Eval uation). In the last stage\, the new model was tested and evaluated in a d esign experiment by examining the performance of external participants whe n applying it. Two categories of success criteria have been planned: appli cability of the process and effectiveness of both the process and its outc ome. Depending on these two categories\, a set of metrics were developed.\ nThe study's conclusions are that the new model\, whose correctness and ef fectiveness are strongly based on the widely-accepted C-K Theory\, present s a clear and concise step-by-step procedure\, is conducive to teaching an d practicing design\, and captures the dynamics and rationale of the conce ptual design process. Thus\, the ICE model has the potential to facilitate creativity and innovation\, as well as high-quality and viable conceptual design\, with respect to the design requirements and other aspects.\nThe significance of the current research is in its contribution to the theory and practice of engineering design\, eventually leading to improved design processes and better designed products. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-430@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170717T163000 DTEND;TZID=Asia/Jerusalem:20170717T173000 DTSTAMP:20230530T180919Z URL:https://aerospace.technion.ac.il/events/experimental-investigation-of- a-boron-loaded-gel-fuel-ramjet-combustor/ SUMMARY:Experimental Investigation of a Boron Loaded Gel Fuel Ramjet Combus tor DESCRIPTION:Lecturer:Irit Tsin-Shwartz\n Faculty:Department of Aerospace En gineering\,\n Institute:Technion – Israel Institute of Technology\n Loca tion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Ab stract: \n Details: \n Nowadays there is a growing demand for improvement in rocket and air-breathing performance and safety. There is a huge potent ial in combining ramjet engines with gel fuel that can carry boron particl es. Ramjet engines combined with gel fuel and metal additives can be used for tactical missiles that can\, theoretically\, reach strategic missile r anges. Gel fuels combine the benefits of both liquid and solid fuels\, in terms of safety and performance.  Moreover\, they allow addition of metal particles without sedimentation\, thus increasing the energetic performan ce.\nIn order to experimentally verify the feasibility of such a concept\, a lab-scale Ramjet combustor was designed and built and a parametric inve stigation was conducted. The test facility included a vitiated air heater to simulate flight conditions and a fuel supply system. The fuel that was used in this research was a kerosene-based gel fuel\, combined with boron powder. More than 150 valid tests were conducted which included various bo ron loadings. The parametric investigation included the effect of pressure \, boron content\, fuel/air ratio and more. The experimental results indic ate that the concept of the Gel Fuel Ramjet combustor is feasible. Recomme ndations for additional research that should be conducted in the future wi ll be presented at the end of the talk. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-431@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170719T163000 DTEND;TZID=Asia/Jerusalem:20170719T173000 DTSTAMP:20230530T180938Z URL:https://aerospace.technion.ac.il/events/development-of-integrated-geom etry-nozzles-for-rocket-motors/ SUMMARY:Development of Integrated Geometry Nozzles for Rocket Motors DESCRIPTION:Lecturer:Lior Miller\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Solid-propellant rocket motors for tactical missiles requir e low cost\, low maintenance level\, immediate availability and high perfo rmance. Their main goal is to supply the required thrust and impulse to th e missile to perform the mission they are designed to.\nAdvanced rocket mo tor nozzles aspire to improve the rocket motor performance by variable mea ns or to increase the system designer freedom\, using non-conventional geo metries.\nAn investigation has been conducted\, experimentally and theoret ically\, to study the effect of changing the rocket motor nozzle cross sec tion from round to rectangular on its ballistics performance. In general\, the experiments showed that the use of rectangular losses results in mino r losses in performance in comparison to axisymmetric nozzles. An adequate rectangular nozzle design can significantly reduce these losses. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-429@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170726T163000 DTEND;TZID=Asia/Jerusalem:20170726T173000 DTSTAMP:20230530T180901Z URL:https://aerospace.technion.ac.il/events/cooperative-multi-robot-belief -space-planning-for-visual-inertial-navigation-and-online-sensor-calibrati on/ SUMMARY:Cooperative Multi-Robot Belief Space Planning for Visual-Inertial N avigation and Online Sensor Calibration DESCRIPTION:Lecturer:Yair Ben-Elisha\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n High accuracy navigation in GPS-deprived uncertain envi ronments is of prime importance to various robotics applications. In such scenarios\, it has been recently shown that online sensor calibration and multi-robot collaboration\, whereby robots make mutual observations of the environment or perform relative observations of each other\, can signific antly enhance navigation accuracy. However\, these approaches typically co nsider a passive setting\, where robot actions are externally determined. On the other hand\, belief space planning (BSP) approaches account for dif ferent sources of uncertainty\, thus identifying actions that improve cert ain aspects in inference\, such as accuracy. Yet\, existing BSP approaches typically do not consider sensor calibration in the mentioned problem set ting\, nor a visual-inertial SLAM setup.\nIn this research\, we contribute a multi-robot BSP approach for active sensor calibration considering a vi sual-inertial SLAM system. To that end\, we maintain a belief over both ro bot's pose and sensor calibration\, and reason how that belief would evolv e for different actions while considering partially unknown and uncertain environments. In particular\, we leverage the recently developed concept o f IMU pre-integration and develop appropriate factor graph formulation for future beliefs to facilitate computationally efficient inference within B SP. Another key aspect of our approach are indirect multi-robot observatio n updates given the states of different robots are correlated. This concep t allows for a subset of robots to carry on their individual (possibly tim e-critical) tasks while preserving high accuracy estimation by relying on other expendable robots to make appropriate observations of the environmen t. We study our approach in high-fidelity synthetic simulation and show th e determined actions can lead to significantly improved estimation accurac y. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-428@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170802T163000 DTEND;TZID=Asia/Jerusalem:20170802T173000 DTSTAMP:20230530T180843Z URL:https://aerospace.technion.ac.il/events/bundle-adjustment-with-feature -scale-constraint-for-enhanced-estimation-accuracy/ SUMMARY:Bundle Adjustment with Feature Scale Constraint for Enhanced Estima tion Accuracy DESCRIPTION:Lecturer:Vladimir Ovechkin\n Faculty:Technion Autonomous System s Program (TASP)\,\n Institute:Technion – Israel Institute of Technology \n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom : \n Abstract: \n Details: \n Accurate pose estimation and 3D reconstructi on are important in a variety of applications such as autonomous navigatio n or mapping in uncertain or unknown environments. Bundle adjustment (BA) and simultaneous localization and mapping (SLAM) are commonly used approac hes to address these and other related problems. Given a sequence of image s\, BA is the problem of simultaneously inferring the camera poses and the observed 3D landmarks. BA is typically solved by minimizing the re-projec tion error between image observations (image features) and their predictio n obtained by projecting the corresponding landmarks onto the camera frame . This optimization is typically realized using non-linear least-squares ( NLS) approaches. Different techniques exist for detecting image features\ , including the well-known SIFT features. Yet\, state of the art BA and vi sual SLAM approaches formulate the constraints in the NLS optimization uti lizing only image feature coordinates.\nIn this work we propose to incorpo rate within BA a new type of constraints that use feature scale informatio n that is readily available from a typical image feature detector (e.g. SI FT\, SURF). While feature scales (and orientation) play an important role in image matching\, they have not been utilized thus far for estimation p urposes in BA framework. Our approach exploits feature scale information a nd uses it to enhance the accuracy of bundle adjustment\, especially along the optical axis of the camera in a monocular setup. Specifically\, we f ormulate constraints between the measured and predicted feature scale\, wh ere the latter depends on the distance from the camera and the correspondi ng 3D point\, and optimize the system variables to minimize the residual e rror in these constraints in addition to minimizing the standard re-proje ction error. We study our approach both in synthetic environments and real -image ground and aerial datasets (KITTI and Kagaru)\, demonstrating signi ficant improvement in positioning error. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-414@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170809T163000 DTEND;TZID=Asia/Jerusalem:20170809T173000 DTSTAMP:20230530T180123Z URL:https://aerospace.technion.ac.il/events/ir-radiometry-of-a-premixed-co 2-air-jet-towards-gas-temperature-reconstruction/ SUMMARY:IR Radiometry of a Premixed CO2-Air Jet Towards Gas Temperature Rec onstruction DESCRIPTION:Lecturer:Matan Jacoby\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The study and optimization of combustion processes require s precise knowledge of the temperature and species’ concentration fields . In such applications\, measurements are often taken locally by intrusive techniques that affect the aero-thermal field of interest and lack spatia l resolution. Thus\, for high fidelity analysis and for physically inacces sible regions\, there is much value in developing non-intrusive measuremen t alternatives.\nIn order to probe combustion processes\, the most promine nt species is CO2\, which radiates within ~4.3µm wavelength band where t he absorption of other atmospheric gases is negligible. This emission of C O2 is considered in context of an axisymmetric free jet\, a common geomet ry of interest - mimicking the exhaust plume of many thermodynamic cycles. By establishing a validated model for CO2 emissivity and developing a me thod which extends radiation thermometry to gases\, the research effort focuses on a measurement technique to reconstruct the temperature distribu tion of a steady jet with known source CO2 and air mixture concentratio ns in the upstream supply line.\nThe experimental setup consists of a free jet produced by an orifice. CO2 - air gasses flow into a mixing chamber\, the flow rates of which are adjusted independently. The mixture temperatu re is regulated by an electric heater. The resulting jet flow temperature is monitored by traverses of a thermocouple probe. The emitted radiation f lux is measured by an IR camera.\nThe HITRAN/HITEMP database\, which inclu des line-by-line spectroscopic parameters for high resolution molecular ab sorption and radiance calculations\, is used to predict and simulate the s pectral emission and transmission of the jet as well as the atmospheric pa th. The species’ diffusion in the jet is modeled via correlation with th e local temperature gradients. Then\, all the unknowns can be related to g eometric variables obtained from integral radiation flux measurements\, an d to local temperature distributions which are optimized to yield minimum deviation from the integral observations.\nGiven an approximation of atmos pheric temperature\, pressure and composition (typically known in most sen sing applications)\, as well as an estimate of upstream CO2 concentration\ , the jet temperature distribution is reconstructed from integral IR camer a radiation flux measurements\, absent of per-scenario calibration. Finall y\, the assumption of known supply CO2 concentration may be relaxed to im prove precision and utility\, by applying additional camera observations w ith multiple optical filters. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-406@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170823T163000 DTEND;TZID=Asia/Jerusalem:20170823T173000 DTSTAMP:20230530T180430Z URL:https://aerospace.technion.ac.il/events/multi-hotwire-probe-sensitivit y-optimization-in-constant-temperature-anemometry-cta-for-transonic-flows/ SUMMARY:Multi-Hotwire Probe Sensitivity Optimization in Constant Temperatur e Anemometry (Cta) for Transonic Flows DESCRIPTION:Lecturer:Efim Yablochkin\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n A simple optimization method is proposed for multi-wire CTA probe design. The optimization computes the sensitivities to density\ , velocity and total temperature for each wire\, based on empirical Nu – M - Re and ƞ – M – Re correlation for heated cylinders in compressi ble flow. This correlation is a reasonable estimator for the compressibili ty effect\, enabling the reduction to M-independent relation. The output i s a set of optimal wire temperatures and diameters\, recommended for probe production. Following the manufacturing\, it is necessary to calibrate ea ch wire for Re - Nu relationship and apply together with the empirical com pressibility relation. The technique allows the use of a single probe with multiple wires across a range of transonic flows with various conditions. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-415@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170830T163000 DTEND;TZID=Asia/Jerusalem:20170830T173000 DTSTAMP:20230530T180152Z URL:https://aerospace.technion.ac.il/events/mixed-dimensional-modeling-of- time-dependent-wave-problems/ SUMMARY:Mixed-Dimensional Modeling of Time-Dependent Wave Problems DESCRIPTION:Lecturer:Hanan Amar\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n It is common to find aerospace structural parts which behave in a one- or two-dimensional manner. This behaviour allows us to simplify the analysis\, in comparison to that which would be required for a fully three-dimensional analysis\, by treating these parts as beams\, plates or shells. However\, in certain cases we may not be able to reduce the dimens ion of the entire structure\, but only a portion of it.\nFor example\, in truss and frame structures\, that are commonly found in aircraft wings\, m ost of the structure exhibits a beam-like behaviour. However\, around the joints connecting the beams we may find a more intricate 3D stress field. If we wish to capture the behaviour at the joints accurately\, we must mod el them as 3D objects. Yet modelling the entire structure in 3D is very co stly. We would like to utilize the 1D aspect of the beam-like substructure s to simplify the model. Other examples for the need for a mixed-dimension al model exist in other fields of application\, like medicine.\nLately var ious hybrid methods have been proposed for solving a coupled high- and low -dimensional problem. These methods involve a mechanism for coupling high- and low-dimensional models. Most of these methods have been developed and applied to static or steady state problems. The current work extends two of these methods to  time-dependent wave problems. We will present the de rivation and numerical implementation of the Nitsche and Panasenko couplin g methods\, as well as results of numerical experiments used assess their performance. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-416@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170906T163000 DTEND;TZID=Asia/Jerusalem:20170906T173000 DTSTAMP:20230530T180213Z URL:https://aerospace.technion.ac.il/events/mechanics-of-3d-printed-deform able-composites/ SUMMARY:Mechanics of 3D-Printed Deformable Composites DESCRIPTION:Lecturer:Adi Batan\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Composite materials play an important role in various enginee ring applications including aerospace industry. This is due to the attract ive mechanical properties and strength-to-weight ratio of composite materi als. Moreover\, these properties can be tailored by designing the microstr uctural arrangements and composition of the heterogeneous materials. Recen t development in the materials fabrication\, in particular multimaterial 3 D printing technologies already allow realization of material designs at d ifferent length-scales.\n\nIn this study\, we specifically focus on the me chanical properties of composite materials produced through the UV assiste d multimaterial 3D printing. In particular\, we focus on the influence of the interphases between different phases on the mechanical performance of the 3D printed composites. We find that while the interphase phenomenon ba rely influence the effective mechanical properties of the composite\, it s ignificantly influence the stability of the material\, as such the critica l strain and associated critical wavelength of elastic instabilities chang e.\n\nTo elucidate the underlining phenomenon\, we employ the finite eleme nt based numerical analysis\, and perform the rigorous Bloch-Floquet insta bility analysis\, while accounting for the interphases. The numerically ob tained critical strains and wavelengths are compared with the experimental results on 3D printed laminates. We observe a good qualitative agreement between the experimental and numerical results. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-411@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170912T103000 DTEND;TZID=Asia/Jerusalem:20170912T113000 DTSTAMP:20230530T180015Z URL:https://aerospace.technion.ac.il/events/three-methods-to-tackle-noise- thermoacoustic-instabilities-and-sensitivity-in-aero-engines-quantum-mecha nics-chaos-theory-and-numerical-simulations/ SUMMARY:Three Methods to Tackle Noise\, Thermoacoustic Instabilities and Se nsitivity in Aero-Engines: Quantum Mechanics\, Chaos Theory and Numerical Simulations DESCRIPTION:Lecturer:Dr. Luca Magri\n Faculty:Engineering Department\n Inst itute:University of Cambridge\, UK\n Location:Classroom 165\, ground floor \, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The dynami cs of aircraft-propulsion flows is difficult to understand because of the intertwined interactions between the acoustics\, combustion and hydrodynam ics. The understanding\, modeling and control of these flows are in consta nt development. In this talk\, the multi-physics of such flows is tackled from angles that are different from the traditional paradigms.\n\nThe gene ration of sound at the combustor’s exit\, which contributes to noise pol lution\, is investigated in the first part of the talk. The question that will be addressed is “Are there sources of sound due to combustion that have not been identified yet?” By considering a multi-component gas\, su ch as that of a combustion chamber\, a new supersonic-nozzle acoustic mode l is proposed. By drawing analogies from Quantum Mechanics\, a solution is found. It is shown that differences in the gas composition generate indir ect noise when accelerated through the nozzle\, which may be louder than t he sound generated by traditional mechanisms.\n\nIn the second part of the talk\, the focus is on the sound waves that are reflected at the combusto r’s exit back to the combustion chamber. These waves may cause thermoaco ustic instabilities\, which are one of the most intractable problems faced by gas-turbine and rocket-motor manufactures. This is due to the sheer nu mber of parameters that come into play and influence the stability. Adjoin t methods and inverse design have recently attracted attention in thermoac oustics because they offer accurate sensitivity information to this sheer number of parameters. With this information\, the control\, probabilistic sensitivities and physical understanding of thermacoustic instabilities\, also in the presence of symmetry breaking\, are enabled. Lyapunov analysis from chaos theory is applied to a turbulent reacting-flow simulation.\n\n The methods presented in this talk are applied to modelling\, control and optimization of reacting\, multi-physical flows in propulsion systems. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-412@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170918T163000 DTEND;TZID=Asia/Jerusalem:20170918T173000 DTSTAMP:20230530T180042Z URL:https://aerospace.technion.ac.il/events/trajectory-planning-and-guidan ce-for-civil-autonomous-aerial-refueling/ SUMMARY:Trajectory Planning and Guidance for Civil Autonomous Aerial Refuel ing DESCRIPTION:Lecturer:Alexander Tsukerman\n Faculty:Technion Autonomous Syst ems and Robotics Program (TASP)\n Institute:Technion – Israel Institute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aerospac e Eng.\n Zoom: \n Abstract: \n Details: \n Civil aerial refueling is a fut uristic concept that was proposed for reducing the environmental impact an d improving the efficiency of long-haul air transportation.  It will allo w a passenger aircraft (the Receiver) to take-off with much less fuel than required to fly the whole route. Dedicated Tanker aircraft will further j oin the Receiver along its route and transfer the required amount of fuel to complete the mission. In such scenario\, the Receiver flies along its o riginal route while the Tanker aircraft is responsible for the execution o f the approach maneuver prior to the deployment of the docking equipment. To ensure smooth and safe aircraft rendezvous\, automation is becoming a n ecessity.\nIn this talk\, two guidance laws to achieve rendezvous between the Tanker and the Receiver will be presented. Both guidance laws were dev eloped using linear quadratic optimal control theory to impose zero termin al relative position\, zero terminal relative flight path angle\, and zero terminal acceleration. The first guidance law was designed as an outer lo op based on a first-order lag model of an inner closed loop airframe respo nse. Analytic solution for this guidance law will be presented and compare d to previously obtained guidance laws. The second guidance law was develo ped as a single loop autopilot-guidance controller\, which is based on a m ore detailed airframe model\, using full state feedback. We will demonstra te\, using a detailed\, nonlinear\, six degrees of freedom simulation\, th e ability of both guidance laws to steer the Tanker aircraft to rendezvous with the Receiver. The performance of both guidance laws will be presente d separately\, for each plane of motion\, in terms of the ability of the g uidance law to shape the aircraft trajectory while inducing small variabil ity in control surface deflections. The comparison study\, carried out for a large set of design parameters using numerical simulations\, indicated that the overall performance can be improved by applying each guidance law for a different plane of motion. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-409@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170925T163000 DTEND;TZID=Asia/Jerusalem:20170925T173000 DTSTAMP:20230530T180446Z URL:https://aerospace.technion.ac.il/events/comparison-of-laboratory-testi ng-techniques-for-replicating-in-flight-dynamic-loads/ SUMMARY:Comparison of Laboratory Testing Techniques for Replicating In-Flig ht Dynamic Loads DESCRIPTION:Lecturer:Kobi J. Cohen\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Modern weapon systems used on high-performance aircraft h ave complex electronic assemblies\, optical components and sensitive mecha nisms that are required to survive and operate in a challenging dynamic en vironment throughout their complete life cycle. The design of these compon ents depends on knowledge of the environmental loads acting on the weapon system during operational conditions. These include aircraft noise induced by engines\, gunfire\, etc.\, mechanical loads induced by aircraft struct ural response to flight conditions (transferred to the system through the pylons)\, and aerodynamic noise induced by turbulent boundary layer and sh ock-boundary layer interaction. The latter is considered to be the most si gnificant source of the in-flight vibratory environment. Aerodynamic noise is expressed as pressure fluctuations in a broadband spectrum (typically up to 10kHz). These loads cause the system to vibrate in a broad spectrum. \nThe development of weapon systems involves extensive laboratory testing\ , designed to substantiate the durability of the hardware in flight-like e nvironmental loads. Various types of laboratory tests are used as experime ntal simulations of in-flight loads\, from direct mechanical vibration tes ts through acoustic tests in reverberant chambers\, or progressive wave tu bes. The question of interest is which testing method\, in terms of bounda ry conditions and excitation type (mechanical or acoustic)\, is most adequ ate to accurately simulate the response of components to flight loads.\nTo answer that question\, a weapon system was tested in mechanical vibration test as well as in acoustic test\, in an attempt to replicate the system ’s acceleration response that was measured in captive flight. In the mec hanical vibration test the system was excited by electro-dynamic shakers\, whereas in the acoustic test\, the excitation was done by loud speakers i n a reverberant chamber. The responses from each test were studied for the ir frequency content\, and compared to the responses measured in captive f light. The seminar will present the tests setups\, results\, the effect of boundary conditions\, and will conclude on the suitability of each test f or studying in-flight loads. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-408@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20170927T163000 DTEND;TZID=Asia/Jerusalem:20170927T173000 DTSTAMP:20230530T180440Z URL:https://aerospace.technion.ac.il/events/monitoring-natural-frequencies -of-composite-structures-as-a-means-to-detect-defects/ SUMMARY:Monitoring Natural Frequencies of Composite Structures as a Means t o Detect Defects DESCRIPTION:Lecturer:Shahar Penias\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Composite materials take a large part in the aerospace in dustry\, and keep getting ever more dominant in air-borne structures. Ther e is at least one field in which composite materials had not yet become as advanced as metals\, and that is NDI. In this work we try to find a solut ion for the problem of interlaminar delaminations in laminate composite ma terials. The aim for this work is developing an on-site (In-situ (method t o be used in order to detect and evaluate a delamination.\nThe method we h ave chosen is a modal analysis of a beam\, in order to detect a change in its natural frequencies\, which will indicate the presence of delamination s. In order to achieve this goal a large amount of numerical analysis alon gside vibration experiments were performed. The end result is a "recipe" f or detecting delaminations using a minimal amount of sensors and equipment . CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-407@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171018T163000 DTEND;TZID=Asia/Jerusalem:20171018T173000 DTSTAMP:20230530T180435Z URL:https://aerospace.technion.ac.il/events/investigation-of-a-morphing-wi ng-capable-of-airfoil-and-span-adjustment-using-a-retractable-folding-mech anism-new-engineering-approach/ SUMMARY:Investigation of a Morphing Wing Capable of Airfoil and Span Adjust ment using a Retractable Folding Mechanism – New Engineering Approach DESCRIPTION:Lecturer:Amit Geva\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n A morphing or adapting aircraft is a term used to define an a irplane that enables mid-flight geometry change\, in order to allow a shif t in performance and aerodynamic traits which in turn would allow for the optimization of multiple flight scenarios. Many viable solutions are exami ned and tested with various degrees of success. Span morphing is commonly used in order to improve duration while airfoil morphing (mostly refers to the camber) is commonly used to allow the elimination of ailerons and fla p aerodynamic disturbances and thus lower parasitic drag. Most span morphi ng solutions are of limited geometry change\, while those who do offer an extreme alteration in span result in a "new" aircraft which has an airfoil that is not suitable for the new working point.\n\nThe proposed solution presented in this work is of a folding\, reversible wing which enables sub stantial wingspan and airfoil alteration simultaneously. The efficiency of such an aircraft is defined and analyzed while a "step by step" procedure is laid out for the process of initial sizing. In addition\, the folding maneuver results in an abnormal airfoil which is examined and wind tunnel tested in order to assess the overall validity of the proposed configurati on. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-410@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171023T163000 DTEND;TZID=Asia/Jerusalem:20171023T173000 DTSTAMP:20230530T180452Z URL:https://aerospace.technion.ac.il/events/seminar-in-memory-of-prof-shmu el-and-mrs-noemi-merhav-full-state-autopilot-guidance-for-multi-input-mult i-output-missile-engagements/ SUMMARY:Seminar in Memory of Prof. Shmuel and Mrs. Noemi Merhav – Full-St ate Autopilot & Guidance for Multi-Input Multi-Output Missile Engagements DESCRIPTION:Lecturer:Dr. Maital Levy\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n There are two main approaches to design autopilot and g uidance systems: “Single-Loop” and “Two-Loop”. In the “Single-Lo op” approach there is no definite autopilot\, and the guidance command i s applied directly to the actuators. In the “Two-Loop” approach the in ner autopilot loop has to follow commands generated by the outer guidance loop\, and each loop is designed separately. The main goal of the research was to identify the merits of each approach\, and combine the benefits of the two approaches into a new improved one.\n\nIn the talk\, the advantag es of the “Two-Loop” and “Single-Loop” approaches will be discusse d. The conditions for obtaining equivalence between the two design approac hes will be presented. Broadly speaking\, an equivalence relation between these two design approaches holds if full-state feedback exists and the nu mber of guidance commands is equal to the number of available controls. Th e equivalence conditions are established under linear quadratic optimal co ntrol and differential game formulations\, and for nonlinear systems with bounded controls. The performance of the “Two-Loop” and “Single-Loop ” approaches to design autopilot and guidance systems is illustrated via simulations. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-32@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171024T110000 DTEND;TZID=Asia/Jerusalem:20171024T120000 DTSTAMP:20221030T083433Z URL:https://aerospace.technion.ac.il/events/inauguration-of-anpl-laborator y/ SUMMARY:Inauguration of ANPL Laboratory DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Lady Davis\, F loor 1\, in the Philadelphia Control Center Facility\n Zoom: \n Abstract: \n Details: \n CATEGORIES:Events LOCATION:Lady Davis\, Floor 1\, in the Philadelphia Control Center Facility END:VEVENT BEGIN:VEVENT UID:0-418@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171025T163000 DTEND;TZID=Asia/Jerusalem:20171025T173000 DTSTAMP:20230530T180253Z URL:https://aerospace.technion.ac.il/events/nonlinear-structural-and-aerod ynamic-modeling-for-static-aeroelastic-analysis/ SUMMARY:Nonlinear Structural and Aerodynamic Modeling for Static Aeroelasti c Analysis DESCRIPTION:Lecturer:Etay Kantor\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The push towards lighter and more efficient aircraft struct ures has led to modern aircraft configurations that are more elastic than ever\, featuring large elastic deformations in their operating conditions . This trend applies to UAV platforms as well as to transport aircraft. Su ch platform might be susceptible to detrimental aeroelastic phenomena that must be accurately analyzed and accounted for in the design process. One shortcoming of modern production aeroelastic analysis and design methods i s that they typically rely on linear structural and linear aerodynamic mod els\, which are not suitable for geometrically nonlinear structures\, of l arge deformations.\nThe current study employs a nonlinear\, modal-based\, structural modeling approach\, together with nonlinear aerodynamic modelin g\, for static aeroelastic analyses. The nonlinear structural model\, int ended for geometrically nonlinear structures of large deformations\, analy zes the deformations of a beam-like structure by dividing it into a small number of segments. Large deformations are treated as the sum of large\, r igid-body displacements of the segment\, plus small\, linear\, elastic def ormation within the segment. The nonlinear aerodynamic modeling approach i s a modified strip theory\, also designed for beam-like structures\, that is based on a database of nonlinear sectional aerodynamic forces. The semi nar will present the two models\, with focus on the nonlinear structural m odel and the intricacies of the application of compatibility equations bet ween segments when using a modal approach.\nThe numerical examples include several load cases that validate the implementation of the methodology a nd demonstrate its use for static aeroelastic applications. Two validation cases include a beam subject to a large follower tip force\, with referen ce to results from commercial nonlinear finite-element solver\, and a wind -tunnel test of a wing with large deformations. The third case is of a hig hly elastic wing subject to large aerodynamic loading. It is used to compa re between the nonlinear and linear structural and aerodynamic modeling ap proaches\, and highlight the effect of nonlinear modeling on the resulting aeroelastic and aerodynamic characteristics. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-420@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171101T163000 DTEND;TZID=Asia/Jerusalem:20171101T173000 DTSTAMP:20230530T180339Z URL:https://aerospace.technion.ac.il/events/experimental-investigation-of- the-hydrogen-peroxide-solid-hydrocarbon-hypergolic-ignition/ SUMMARY:The Timnat Prize Seminar - Experimental Investigation of the Hydrog en Peroxide – Solid Hydrocarbon Hypergolic Ignition DESCRIPTION:Lecturer:David Andres Castaneda\n Faculty:Department of Aerospa ce Engineering\n Institute:Technion – Israel Institute of Technology\n L ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The research examines the idea of using hypergol ic ignition in a hybrid motor. The main advantages of the hybrid motor are the facts that it is simple\, controllable and exhibits shut-off and re-i gnition capability. The ignition delay between the fuel and the oxidizer h as to be minimal and provide the adequate heat release to assure combustio n.\nHydrogen peroxide is considered as an excellent oxidizer in hybrid sys tems. Wernimont and Heister investigated the performance of a hybrid rocke t motor that used hydrogen peroxide and polyethylene. Ignition was achieve d by using a catalytic bed\, which decomposed hydrogen peroxide and allowe d the fuel to burn with the oxidizer. However\, the introduction of a cata lytic bed increases weight and affects the performance of the motor.\nThe ignition of the solid hydrocarbon fuel (HTPB or PE) in a hybrid system can be accomplished by utilizing a hypergolic combination of oxidizer and fue l. For an efficient hybrid system\, the ignition of the fuel grain has to be fast and effective\, i.e.\, to obtain low ignition delay and high heat release. High performance materials and direct hypergolic ignition between the solid fuel and the oxidizer seems to be a suitable solution for the m entioned above. Research has been conducted on the ignition delay obtained from the hypergolic ignition of gelled kerosene with suspended catalyst/r eactive particles as done by Natan et al\, showing that the addition of ca talyst in a gelled inert fuel can allow efficient hypergolic ignition.\nTh at same idea can be implemented in a hybrid motor in which the catalyst is embedded in the solid fuel to allow ignition upon contact with the hydrog en peroxide. Within the frame of the present work the ignition delay and f easibility of a hypergolic ignition between a liquid oxidizer and a solid hydrocarbon fuel was investigated. Various catalysts and fuel types at dif ferent conditions have been studied. The effects of the concentration of t he catalyst in the fuel\, the fuel temperature and the ambient pressure on the ignition delay were investigated.\nThis was done by conducting drop-o n-solid tests in a combustion bomb in which the ignition delay was measure d using a high-speed camera.\nThe results indicate that this solution can be implemented to obtain a hybrid hypergolic igniter. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-421@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171106T163000 DTEND;TZID=Asia/Jerusalem:20171106T173000 DTSTAMP:20230530T180624Z URL:https://aerospace.technion.ac.il/events/optimal-target-defensive-strat egies-against-multiple-pursuers/ SUMMARY:Optimal Target Defensive Strategies against Multiple Pursuers DESCRIPTION:Lecturer:Zheng Wen Tan\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n In this talk\, we will present our research on cooperativ e optimal defensive strategies in multiple-vehicle engagements. Specifical ly\, we consider the scenario in which two target aircraft are being pursu ed by two missiles. A novel defensive guidance law will be presented in wh ich the target pair maneuvers cooperatively to lure their pursuers into co llision. Unlike defensive strategies such as evasion or deploying defender missiles\, the proposed guidance law does not require the targets to have acceleration advantage over their pursuers nor do they need to carry addi tional missiles.\nThe talk will be split into two sections.  In the first section\, derivation of the cooperative guidance law based on linear quad ratic optimal control theory will be presented. The derivation of the opti mal cooperative strategy assumes that the pursuing missiles are using line ar guidance laws and all vehicles have constant speeds with arbitrary-orde r linear dynamics. We will demonstrate the performance of the cooperative strategy when using perfect state information through a “collision map ”.  This map highlights the ability of the proposed guidance law to lur e the missiles into collision over a range of initial conditions. In the s econd part of the talk\, we will consider the case when the targets have i mperfect information on the missiles’ states and guidance laws. Here we will present a decentralized estimation/ identification scheme that is bas ed on the multiple model adaptive estimation (MMAE) approach. However\, un like the conventional MMAE approach in which the number of required filter s for guidance law identification grows quadratically with the number of p ossible missile guidance strategies\, number of filters in the proposed sc heme only grows linearly and is computationally more efficient. Missile-mi ssile miss distance performance of the cooperative guidance law with estim ator-in-the-loop will be demonstrated through a Monte Carlo simulation stu dy in which we will also highlight its sensitivity to missile-target range estimation error. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-422@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171108T163000 DTEND;TZID=Asia/Jerusalem:20171108T173000 DTSTAMP:20230530T180642Z URL:https://aerospace.technion.ac.il/events/customized-droplet-density-in- double-emulsions/ SUMMARY:Customized Droplet Density in Double Emulsions DESCRIPTION:Lecturer:Shaik Subhani\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n The generation of monodisperse tracer particles is a cruc ial element of particle image velocimetry (PIV) flow measurements\, but mo st commercially available particles are expensive to purchase\, difficult to manufacture in-house\, or fail to provide the neutral or near-neutral b uoyancy needed to obtain unbiased velocity measurements. In this study\, w e seek to generate custom PIV particles by a double-emulsion method\, in w hich the density and light-reflecting or light-emitting properties of the tracer droplets can be modified with relative ease and the monodispersity of the droplets can be controlled. The double emulsion droplets are genera ted by a co-flow microfluidic device. The micro-capillary device consists of cylindrical glass capillaries nested inside a square capillary.  This involves a single step generation of double emulsions with precise control over size of the droplets.\nThe formation of double emulsion droplets is via two mechanisms i.e\, dripping and jetting. In the dripping regime\, th e droplet forms close to the entrance of the collector capillary whereas i n the jetting regime the inner and the middle fluid form a co-axial jet wh ich extends two and more capillary diameters and breaks into a chain of do uble emulsion droplets. The flow rates and fluid properties of the droplet manufacturing process were optimized and the effect of density modificati on by salt addition was studied.  The double emulsion droplets are polyme rized using photo-polymerization techniques. Finally\, the droplets were u sed in preliminary PIV measurements. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-50@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171109T090000 DTEND;TZID=Asia/Jerusalem:20171109T100000 DTSTAMP:20221030T083434Z URL:https://aerospace.technion.ac.il/events/the-16th-israeli-symposium-on- jet-engines-and-gas-turbines/ SUMMARY:The 16th Israeli Symposium on Jet Engines and Gas Turbines DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Auditorium (ro om 235)\, Faculty f Aerospace Engineering\, Technion\, Haifa\n Zoom: \n Ab stract: \n Details: As in previous years\, we plan to hold a symposium on Jet engines and gas turbines as well as a two-day workshop on relevant top ics. The 16th Symposium will be held in the building of the faculty of Aer ospace Engineering at the Technion on November 9\, 2017. The workshop will be held two days earlier\, on Tuesday\, November 7\, 2017. Following is t he call for the Symposium. As for the workshops\, a separate leaflet will be distributed after the exact topics of the workshops will be determined. In the meantime we recommend to secure these two dates.\nFor the program of the symposium\, please click here.\nI hope to see you participating in the symposium\, and even more participating as lecturers.\nLooking forward to seeing you in the symposium\,\nYeshayahou Levy\,\nChairman of the 16th Symposium on Jet Engines and Gas Turbines\n\n[caption id="attachment_1430 6" align="alignnone" width="300"] Photo from the 15th Israeli Symposium on Jet Engines and Gas Turbines[/caption]\n\n[caption id="attachment_14304" align="alignnone" width="300"] Photo from the 15th Israeli Symposium on Je t Engines and Gas Turbines[/caption]\n\n[caption id="attachment_14318" ali gn="alignnone" width="300"] Photo from the 15th Israeli Symposium on Jet E ngines and Gas Turbines[/caption]\nTHE 16TH ISRAELI SYMPOSIUM ON JET ENGIN ES AND GAS TURBINES\nThursday\, November 9 \,2017 (9:00-17:00)\,\nAuditori um (room 235)\, Faculty f Aerospace Engineering\, Technion\, Haifa\nThis year\, as in the previous 15 years\, we plan to hold the Israeli Symposium on Jet Engines and Gas Turbines. During the last few years there has seen a steady expansion of activities in Isreal in turbo jet propulsion. This is in addition to the serial production of small engines\, increased elect ricty generation using gas turbines and combined cycles\, production of va rious engines' spare parts and maintenance work. In Israel\, many bodies a re active in jet engines and gas turbine area\, including: MAFAT (MoD)\, I AF\, Israel Navy\, EL-AL\, IAI\, Beit Shemesh Engines\, RAFAEL\, TAAS\, OR MAT\, Israel Electric Corporation\, R-Jet &\; Becker Engineering\, the Technion and more.\nImproved engineering &\; technological innovations and new projects in Israel calls for continued professional meetings’ fo r the exchange of information\, for cross-pollination and for creating a f ertile seedbed for cooperation. During the previous 15 symposia\, in every one\, more than hundred scientists and propulsion engineers met and prese nted their work from the various industries\, the MoD and Academia. These symposia were a success\, wetting the appetite for more such meetings.\nTh e 16th symposium will include invited introductory lectures on selected su bjects (from large engine manufacturers and Academia). In addition there w ill also be presentations that concern activities in different Israeli ind ustrial firms\, institutes and\, upon request\, a tour to the faculty's re novated Turbo and jet Engine laboratory. This will also be a good opportun ity for professional meetings\, exchange of ideas and presentation of jet engine models and products from various companies.\nDuring the symposium t here will be an opportunity to discuss all topics relevant to jet engines and gas turbines\, including innovative cycles\, aerodynamics of turbo-mac hines\, combustion\, heat transfer\, structures and dynamics\, simulations \, control\, production processes and maintenance\, combined cycles and mo re. Preference will be given to subjects of interest in Israel.\nTypically \, the first half of the symposia (till lunch time) will be held in Englis h.\nPlease note that the presentation from the 15th symposium can be seen in the following (Technion’s Jet Engine laboratory’s) website:\nhttps: //jet-engine-lab.technion.ac.il/\nPrice per person for early registration is 250 NIS (registration fee includes lunch and book of abstracts). Full t ime students (graduate and undergraduates) are granted with free symposium registration (but without the lunch…). Payment to the symposium should be sent in advance by check\, payable to "Technion"\, addressed as listed below.\nIn special cases\, one can register on the day of the symposium.\n Presentations will be published in full\, or as a "censored" version\, aft er the conference on the conference website. In addition there will be an opportunity to present/display promotional material.\nPlease contact the u ndersigned for this purpose.\nThose who wish to participate are asked to r egister by e-mail\, before September 1st\, 2017 to the following address:  aejetlab@technion.ac.il\nLooking forward to seeing you at the symposium\ ,\nProfessor Yeshayahou Levy\nChairman of the symposium\nlevyy@technion.ac .il\n CATEGORIES:Events LOCATION:Auditorium (room 235)\, Faculty f Aerospace Engineering\, Technion \, Haifa END:VEVENT BEGIN:VEVENT UID:0-417@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171115T163000 DTEND;TZID=Asia/Jerusalem:20171115T173000 DTSTAMP:20230530T180234Z URL:https://aerospace.technion.ac.il/events/an-adaptive-method-for-simulat ion-of-delamination-in-composite-materials/ SUMMARY:An Adaptive Method for Simulation of Delamination in Composite Mate rials DESCRIPTION:Lecturer:Dr. Ofir Shor\n Faculty:\n Institute:Rafael Advanced D efense Systems LTD\n Location:Classroom 165\, ground floor\, Library\, Aer ospace Eng.\n Zoom: \n Abstract: \n Details: \n The use of composite mater ials in engineering applications requiring peak performance and superior r eliability is growing rapidly. Failure of these materials is often charact erized by the onset and progression of distinct damage mechanisms that int eract with each other and yield a complex material behavior during loading \, which poses a serious challenge when attempting to numerically simulate their behavior.\nDuring this seminar\, the major failure mechanisms of co mposites will be described\, followed by a description of the challenges o f simulating these failure modes in large scale structures. Efficient cutt ing-edge numerical technologies aimed to allow damage propagation simulati on in composites will be presented\, followed by static and dynamic exampl e problems. The seminar would also describe some of the latest research ac tivities performed in Rafael related to this field\, with the clear vision of collaborating with the Technion in the exciting field of composite mat erials research. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-413@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171206T163000 DTEND;TZID=Asia/Jerusalem:20171206T173000 DTSTAMP:20230530T180102Z URL:https://aerospace.technion.ac.il/events/if-active-flow-control-afc-is- to-become-a-design-tool-in-aerodynamics-do-we-need-to-depart-from-prandtls -classical-approach/ SUMMARY:If Active Flow Control (AFC) is to Become a Design Tool in Aerodyna mics\, Do We Need To Depart From Prandtl’s Classical Approach? DESCRIPTION:Lecturer:Prof. Israel Wygnanski\n Faculty:Department of Aerospa ce & Mechanical Engineering\n Institute:University of Arizona\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Boundary layer control by blowing enabled early combat je t airplanes to operate from shorter runways by increasing their lift coeff icient at low speeds. The concepts of boundary layer and circulation contr ol evolved at that time however\, blowing was never considered interactive ly with other wing design parameters that were separated from each other d ue to the boundary layer approximation. The need for increased speed resul ted in swept-back planforms that were more recently modified to trapezoida l and lambda shapes for enhanced maneuverability and reduced observability \, while commercial transport wings hardly changed during the past fifty y ears. Sweep back resulted in a pitch-up problem at low speeds that serious ly limited cruise performance. It was traditionally alleviated by swinging the wing forward and adding leading edge devices that increased the weigh t and the complexity of the airplane. This problem could be alleviated by AFC. Furthermore\, AFC can provide control authority around all three axes by itself and in conjunction with conventional control surfaces. To that end\, AFC should be considered at the beginning of the design process and not after its completion.  Such a change in approach recognizes the inter actions among the traditional design parameters and AFC\, simply stating t hat forces and moments acting on a wing depend on its shape\, on its attit ude and on AFC concomitantly. These variables are of comparable value and they should not be treated separately no matter how many parameters are re quired to define them. Experiments carried out on swept wings and tailless aircraft models indicate how AFC has to be tailored in order to avoid pit ch-up with an increase in incidence. Such tailoring does not have to be li mited to momentum or mass-flow input levels that may be traded off in favo r of a change in location and/or orientation of the AFC input. However\, t he payoff is large because a small input may double the usable lift coeffi cient when the latter is needed on a landing approach. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-419@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20171224T100000 DTEND;TZID=Asia/Jerusalem:20171224T110000 DTSTAMP:20230530T180320Z URL:https://aerospace.technion.ac.il/events/plasma-surface-interactions-an d-accelerated-life-testing-the-key-technology-challenges-in-the-developmen t-of-gridded-ion-engines/ SUMMARY:Plasma Surface Interactions and Accelerated Life Testing – The Ke y Technology Challenges in the Development of Gridded Ion Engines DESCRIPTION:Lecturer:Prof. Stephen Gabriel\n Faculty:Department of Aeronaut ics and Astronautics\n Institute:University of Southampton\, Southampton\, UK and Mars Space Ltd\, UK\n Location:Asher Space Research Institute (ASR I) seminar room\n Zoom: \n Abstract: \n Details: \n The talk will present an overview of the research activities on Electric Propulsion (EP) and oth er low temperature plasma technologies at both the university of Southampt on and Mars Space Ltd\, focusing on some of the key challenges.\nThe unive rsity has been active in EP for nearly 30 years\, while Mars Space was spa wned as a spin-off around 10 years ago. How the two organizations have col laborated as partners will be described with an attempt to bring out some of the successes but also some of the potential problems.\nHistorically\, EP research at the university has included gridded ion engines(GIEs)\, hol low cathodes(HCs) and hollow cathode thrusters(HCTs)\, pulsed plasma thrus ters(PPTs) and microcolloid thrusters. Current activities are centred arou nd heaterless hollow cathodes\, alternative propellants for GIEs and liqui d PPTs. Some of the terrestrial applications of low temperature plasmas wh ere there is some synergy with EP are plasma antennas and triggered vacuum arcs.\nAt Mars Space\, the main research areas are broadly similar but mo re of a developmental nature and in close collaboration with industry. Key areas include the development of a ring cusp(RC) GIE with QinetiQ and a G IE hollow cathode neutralizer with Ariane Group but work is also ongoing o n a high temperature resistojet with the possibility of future efforts on an arcjet with Nammo. CATEGORIES:Seminars LOCATION:Asher Space Research Institute (ASRI) seminar room END:VEVENT BEGIN:VEVENT UID:0-389@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180101T163000 DTEND;TZID=Asia/Jerusalem:20180101T173000 DTSTAMP:20230527T140922Z URL:https://aerospace.technion.ac.il/events/the-aeromechanics-of-an-autono mous-multi-multirotor-uav-system-for-payload-transportation/ SUMMARY:The Aeromechanics of an Autonomous Multi-Multirotor UAV System for Payload Transportation DESCRIPTION:Lecturer:Anton Cooper\n Faculty:Technion Autonomous Systems Pro gram (TASP)\n Institute:Technion – Israel Institute of Technology\n Loca tion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Ab stract: \n Details: \n Unmanned Aerial Vehicles (UAVs) are known to be adv antageous for many applications in security\, monitoring of natural risks of environment\, management of ground installations\, and agriculture. In recent years\, the share of autonomous payload transportation by rotary-wi ng UAVs is growing rapidly as well. Such vehicles allow operation in limit ed and confined environments\, urban areas or even indoor sceneries. Yet\, the implementation of such systems is limited due to the limited lifting capabilities of most of the existing hovering vehicles.\nWe address this i ssue by utilizing a slung-load approach in which the payload is hauled by multiple quad-rotors. The idea is to explore the possibility to use such “of-the-shelf” vehicles that were originally designed to operate indep endently\, and connect them by cables to a payload in order to perform a c ooperative transportation mission. In such a system\, each vehicle is inde pendently assigned with a trajectory while treating cable forces as additi onal external disturbance loads. This setting naturally raises questions r egarding its feasibility and characteristics. However\, if this system is indeed feasible\, it constitute a valuable and extremely modular and effec tive arrangement for a variety of payloads by non-dedicated vehicles while the number of UAVs that are assigned for each mission is changed accordin g to the payload weight\, while no further adjustments are required. In th e current study\, a multiple quadrotor-single payload (MQSL) transportatio n system is analyzed using numerical simulative approach.\nAs opposed to t he common “constant rotor force coefficients approach”\, the quadrotor dynamics is modeled using detailed rotor aerodynamics\, which is founded on an extended Blade-Element-Theory and enables simulation of unique and i mportant flight regimes such as slow descent and gusty conditions. Additio nal feature of the present modeling is a refined cable simulation. This mo del consists of breaking the cable into finite segments which are elastica lly connected along with a local aerodynamic drag model for each segment. These enable simulation of the cable bending modes and a capability to sim ulate loose cables\, which are typically not taken into account in full-sc ale helicopter slung-load models. Stability analysis and typical normal mo des of the system will be presented. The suggested methodology includes an extension of feedback linearization control algorithm for quadrotor vehic les\, in addition to a trajectory scheduling algorithm for individual quad rotor vehicle.\nWithin the validity checks of the proposed setting\, the M QSL dynamics and control simulation was also successfully integrated with a Rapidly-exploring random tree (RRT) path planning algorithm. This algori thm provides collision free\, reference path in a tight and confined urban and indoor environments.\nSeveral examples of transportation scenarios\, of pre-defined trajectories such as circular motion\, slalom and "bug trap escaping path” will be demonstrated. The results of the present simulat ive study of MQSL systems give rise to a cautious optimism about the possi bility of implementing such systems for modular payload transportation. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-391@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180103T163000 DTEND;TZID=Asia/Jerusalem:20180103T173000 DTSTAMP:20230527T141000Z URL:https://aerospace.technion.ac.il/events/integrated-guidance-estimation -in-linear-quadratic-differential-games/ SUMMARY:Integrated Guidance / Estimation in Linear Quadratic Differential G ames DESCRIPTION:Lecturer:Barak Or\n Faculty:Department of Aerospace Engineering \n Institute:Technion – Israel Institute of Technology\n Location:Classr oom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Differential Games for pursuit evasion problems have been inve stigated for many years. Differential games\, with linear state equations and quadratic cost functions\, are called Linear Quadratic Differential Ga me (LQDG). In these games\, one defines two players a pursuer and an evade r\, where the former aims to minimize and the latter aims to maximize the same cost function (zero-sum games). The main advantage in using the LQDG formulation is that one gets Proportional Navigation (PN) like solutions w ith continuous control functions. One approach which plays a main role in the LQDG literature is Disturbance Attenuation (DA)\, whereby target maneu vers and measurement error are considered as external disturbances. In thi s approach\, a general representation of the input-output relationship bet ween disturbances and output performance measure is the DA function (or ra tio).  This function is bounded by the control.\nThis work revisits and e laborates upon this approach.  The work contains an introduction of a rep resentative case study\, a “Simple Boat Guidance Problem” (SBGP)\, wit h perfect and imperfect information patterns. By the derivation of the ana lytical solution for this game\, and by running some numerical simulations \, we developed the optimal solution based on the critical values of the D A ratio. Moreover\, we will study a Missile Guidance Engagement (MGE) prob lem\, with and without Trajectory Shaping (TS). The qualitative and quanti tative properties of the MGE solution\, based on the critical DA ratio\, w ere studied by extensive numerical simulations\, and are shown to be diffe rent than the fixed DA ratio solutions. The various factors that influence the choice of parameters for choosing the optimal Trajectory Shaping matr ix will be introduced. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-394@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180117T163000 DTEND;TZID=Asia/Jerusalem:20180117T173000 DTSTAMP:20230527T141055Z URL:https://aerospace.technion.ac.il/events/experimental-investigation-of- a-hypergolic-hybrid-motor/ SUMMARY:Experimental Investigation of a Hypergolic Hybrid Motor DESCRIPTION:Lecturer:David Andres Castaneda\n Faculty:Department of Aerospa ce Engineering\n Institute:Technion – Israel Institute of Technology\n L ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Hybrid rocket systems have the potential to high performance and wide operational capabilities\, as well as throttling and shutdown. An essential component in any rocket system is the ignition mec hanism. This can allow the motor to initiate proper burning\, as well as p rovide ignition - shutdown- re-ignition capabilities. Currently\, the igni tion of hybrid motors is generally achieved by the addition of external ga s or liquid systems\, or by a consumable catalytic bed (CCB)\, resulting i n more complex and heavy systems.\nIn the present work\, a hypergolic hybr id rocket motor is proposed to obtain a more efficient hybrid propulsion s ystem. The hypergolic ignition proposed\, i.e.\, ignition of the fuel upon contact with the oxidizer\, allows very short ignition delay times and sh utdown – re-ignition capabilities without any need of external systems t hat add weight\, length and complexity to the system. The hypergolic ignit ion is achieved by embedding a catalyst\, or promoter\, which is hypergoli c with the liquid oxidizer\, into the solid grain. The hypergolic reaction between catalyst and oxidizer is highly exothermic\, and enough\, to caus e the ignition and combustion of the solid fuel together with the liquid o xidizer. In the present work\, different catalysts and fuels were tested w ith high concentration hydrogen peroxide via drop-on-solid tests and radia l injection\, to prove the feasibility of such ignition.\nThe idea of hype rgolic ignition between a solid fuel and a liquid oxidizer was proven unde r different ambient conditions for different fuels. Average ignition delay times in the tests performed were always less than 10 ms\, depending on the fuel and catalyst load in the solid grain. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-390@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180124T163000 DTEND;TZID=Asia/Jerusalem:20180124T173000 DTSTAMP:20230527T140941Z URL:https://aerospace.technion.ac.il/events/cluster-keeping-with-different ial-drag-and-srp-for-elliptic-orbits/ SUMMARY:Cluster-Keeping with Differential Drag and SRP for Elliptic Orbits DESCRIPTION:Lecturer:Evgeney Koretsky\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n Solar radiation pressure (SRP) is a caused by photons transferring their momentum to the satellite. The magnitudes of atmospheri c drag and SRP are similar for spacecraft in circular orbits at altitudes of about 700 km. SRP tends to increase the eccentricity of the orbit\, whi le atmospheric drag tends to decrease it.  In the present research\, feed back control laws aimed at keeping a cluster of satellites within bounded distances are derived. Differential accelerations are obtained based on cr oss section area manipulation with respect to the drag and SRP directions. By the derivation of a semianalytical solution for the orbital dynamics t hat includes SRP and drag\, we present several improvements to existing cl uster keeping control laws.  The feedback is based on mean semimajor axis \, eccentricity and inclination\, which are obtained from the Brouwer tran sformation. Simulations show that the combination of differential drag and differential SRP can maintain a cluster of satellites within bounded dist ances on highly elliptic orbits\, such as geostationary transfer orbits\, and on circular low Earth orbits. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-392@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180129T163000 DTEND;TZID=Asia/Jerusalem:20180129T173000 DTSTAMP:20230527T141017Z URL:https://aerospace.technion.ac.il/events/investigation-of-the-burning-r ate-of-solid-propellants-composed-of-nano-aluminum-and-water/ SUMMARY:Investigation of the Burning Rate of Solid Propellants Composed of Nano-Aluminum and Water DESCRIPTION:Lecturer:Shahar Wollmark\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n Solid propellants comprised of aluminum and water show high theoretical energetic performance and are considered environmentally friendly\, since the burning products contain non-toxic and carbon-free ma terials (aluminum oxide – Al2O3\, and hydrogen gas – H2). These prope llants may be attractive for different types of propulsion systems (for ex ample: in-space\, under-water)\, and could also be used in other applicati ons\, such as hydrogen production\, power generation etc. Thermochemical a nalysis shows that stoichiometric combustion of aluminum-water propellant can yield high performance parameters that exceed those of the highly toxi c hydrazine at similar conditions\, and are on par with commonly used soli d propellants (AP/HTPB\, NG/NC and others).\nIn the present research\, sol id propellants containing distilled water and different nano‑aluminum po wders were filled into consumable strands\, and ignited inside a pressure chamber for burning rate measurements at pressures up to 70 bar. Three typ es of nano aluminum powders were tested: ALEX – uncoated particles\; V ‑ALEX – Viton coated particles\; and L‑ALEX – stearic acid coated particles. All tested compositions presented burning rates similar to thos e of conventional solid propellants\, and the obtained pressure exponents suggest that the combustion of aluminum-water solid propellants will be st able during pressure fluctuations. In addition to burning rate experiments \, selected compositions were tested inside a small rocket motor where the operating pressure and the developed thrust were measured\, to receive th e key performance parameters of the propellant.\nThe entire process of the research will be covered in the presentation: starting from the powder an alysis using TEM/TGA techniques\; followed by the preparation process of t he different propellant mixtures\; description of the experimental setup c onstructed for the burning rate measurements and the static firing experim ents\; and the results obtained including the performance parameters for t he different propellant compositions. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-54@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180130T132000 DTEND;TZID=Asia/Jerusalem:20180130T151000 DTSTAMP:20221030T083435Z URL:https://aerospace.technion.ac.il/events/space-plasma-propulsion-and-te chnology-workshop/ SUMMARY:Space Plasma Propulsion and Technology Workshop DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Tel-Aviv Unive rsity\n Zoom: \n Abstract: \n Details: Plasma propulsion is becoming one o f the main drivers in lowering cost of space missions. In this workshop ex perts will present their recent research\, followed by a discussion about current and future trends in this growing field\, with emphasis on plasma propulsion for small spacecraft and nanosatellites.\n\nThe Space Plasma Pr opulsion and Technology Workshop will be held on the 30.01.18 (13:20 - 15: 10) in Tel-Aviv University as part of the 13th Ilan Ramon International Sp ace Conference.\nTo register to the workshop please contact Asst. Prof. Ig al Kronhaus at kronhaus@technion.ac.il\n CATEGORIES:Events LOCATION:Tel-Aviv University END:VEVENT BEGIN:VEVENT UID:0-396@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180131T163000 DTEND;TZID=Asia/Jerusalem:20180131T173000 DTSTAMP:20230527T141130Z URL:https://aerospace.technion.ac.il/events/hydrodynamic-stability-in-shar ks/ SUMMARY:Hydrodynamic Stability in Sharks DESCRIPTION:Lecturer:Alon Dahan\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Most sharks are heavier than the water they swim in and ther efore must generate hydrodynamic lift to compensate for the lack of buoyan cy. To this end\, they can use many possible combinations of fins\, includ ing the tail. This multitude of options is responsible for a long-standing debate about how the sharks distribute the lift along their body and fins .  It also raises a question of stability: are sharks stable?\nIn this st udy\, we address both questions using a combined theoretical/numerical/ ex perimental approach. We use wind tunnel experiments and CFD simulations to construct a hydrodynamic model of the Great Hammerhead shark (Sphyrna mok arran). We use this model in a standard ‘flight mechanics’ type analys is to assess its dynamic stability and identify its trim options.\nWe show that the shark’s body cannot provide the necessary lift by itself and m ost of the lift comes from its fins (mostly the pectoral fins) with the ta il providing a sizeable (10 to 30%) portion of the lift for balance. We al so show that the shark is unstable\, and needs an active control to keep i ts trim. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-393@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180214T163000 DTEND;TZID=Asia/Jerusalem:20180214T173000 DTSTAMP:20230527T141037Z URL:https://aerospace.technion.ac.il/events/the-time-dependent-combustion- of-a-gel-fuel-droplet/ SUMMARY:The Time Dependent Combustion of a Gel Fuel Droplet DESCRIPTION:Lecturer:Arza Hadad\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Gel fuels are non-Newtonian fluids with a yield stress. In t he absence of sufficient shear stress\, the gel has a solid-like behavior. Under shear stress the viscosity decreases to allow the atomization and s ubsequent vaporization and combustion\, not much unlike the vaporization a nd combustion of liquid fuels.\nIn terms of safety\, gel fuels exceed both solid and liquid propellants. Moreover\, gel fuels have significant advan tages in terms of performance. As in the case of liquid fuels\, the flow r ate of a gel fuel to the combustion chamber is controllable. In addition\, gel fuels are ideal for energetic additives. Energetic additives\, such a s metal particles\, compensate for the loss in energy content due to the a ddition of the gellant.\nThe present work deals with the mathematical mode ling and numerical simulation of the combustion of a single droplet of gel fuel based on organic gellant. Organic-gellant-based gel fuel drops exhib it a cyclic combustion mechanism. The process begins with a traditional co mbustion\, followed by the formation of an elastic impermeable film of gel lant around the droplet. As a result\, vapor fuel bubbles form and expand inside the droplet until the fuel vapors burst through the film. This proc ess repeats itself until complete depletion of the fuel and gellant. This behavior occurs because the gel fuel is basically a mixture of species wit h very different volatilities: the gellant on one hand and the parent liqu id fuel on the other. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-399@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180226T163000 DTEND;TZID=Asia/Jerusalem:20180226T173000 DTSTAMP:20230530T180352Z URL:https://aerospace.technion.ac.il/events/maximum-conditional-probabilit y-stochastic-controller-for-linear-systems-with-additive-cauchy-noises/ SUMMARY:Maximum Conditional Probability Stochastic Controller for Linear Sy stems with Additive Cauchy Noises DESCRIPTION:Lecturer:Nati Twito\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n The majority of practical estimation and control solutions a re based on system models with additive Gaussian noises. Gaussian distribu tion\, being light tailed\, does not capture significant fluctuations that occur in many engineering applications\, such as atmospheric noises and a ir turbulence\, underwater acoustic noises and image processing. It was sh own that those noises are better described by heavy tailed distributions t hat exhibit significant impulsive characteristics. The heavy tailed distri butions are characterized by probability density functions with tails that are not exponentially bounded. Named after the French mathematician\, Aug ustin Louis Cauchy\, the heavy-tailed Cauchy distribution has been shown t o much better represent this type of fluctuations. The challenge of using this distribution is that it does not have a moment generating function. S pecifically\, its first moment is not well defined and its second and high er moments are infinite.\nIn the recent years\, progress was reported in t he area of estimation of linear systems with additive Cauchy noises. As pa rt of its solution\, the estimator computes explicitly the conditional pro bability density function (pdf) of the state given the measurement history \, or its characteristic function. Those were used to derive a stochastic optimal-predictive controller for the system. Although demonstrating good performance characteristics\, the proposed controller was shown to entail high numerical complexity. This motivated the alternative approach present ed in the current study.\nIn this work a stochastic controller\, inspired by the sliding mode control methodology\, is proposed for linear systems w ith additive Cauchy distributed noises. The design goal is to maximize the prior probability of the system state or its linear combination to be wit hin a given bound around the regulation point. The control law utilizes th e time propagated pdf of the system state given measurements that is compu ted by the Cauchy estimator. The single-state controller was derived using two equivalent implementations: one that relies directly on the above men tioned prior pdf while the second uses the characteristic function of that pdf. The latter was addressed mainly because in the multi-state case only the characteristic function can be determined by the respective Cauchy es timator. The controller performance was evaluated numerically\, and compar ed to an alternative approach presented recently and to a Gaussian approxi mation to the problem. A fundamental difference between the Cauchy and the Gaussian controllers is their response to noise outliers. While all contr ollers respond to process noises\, even to the outliers\, the Cauchy contr ollers drive the state faster towards zero after those events. On the othe r hand\, the Cauchy controllers do not respond to measurement noise outlie rs\, while the Gaussian does. The newly proposed Cauchy controller exhibit s similar performance to the previously proposed one\, while requiring low er computational effort\, and is much easier to implement. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-401@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180305T163000 DTEND;TZID=Asia/Jerusalem:20180305T173000 DTSTAMP:20230530T180404Z URL:https://aerospace.technion.ac.il/events/analysis-and-design-of-microst ructures-in-3d-printed-soft-composites-and-its-implementation-in-morphing- wing-structures/ SUMMARY:Analysis and Design of Microstructures in 3D-Printed Soft Composite s and its Implementation in Morphing Wing Structures DESCRIPTION:Lecturer:Dmitry Vladimirsky\n Faculty:Department of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abs tract: \n Details: \n Rapid development of additive technologies expands n ew horizons in the field of soft robotic¹ design. These technologies are new\, which implementations\, in the field of aerospace\, are incompletely described.\n\nThe presented research intends to show possible application of 3D-printing technique in morphing wing mechanisms production. Two main methods of actuating global response of the composites\, with stiff layer s embedded in the soft matrix\, were considered and developed. The first m ethod is based on local indention that provides programmed global displace ment (the results of numerical simulations fit experimental study). A part of the research included designing several actuators\, would be beneficia l for this type of shape-changing soft structures. The second method is ba sed on a single wire actuated structure\, that has a potentially array of applications due to the structure’s ability to play the role of a counte r-body\, by storing elastic energy.\n\n___________\n\n¹Subfield of robot ics dealing with constructing robots from highly compliant materials. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-400@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180307T163000 DTEND;TZID=Asia/Jerusalem:20180307T173000 DTSTAMP:20230530T180358Z URL:https://aerospace.technion.ac.il/events/numerical-simulation-of-a-boro n-loaded-gel-fuel-ramjet-combustor/ SUMMARY:Numerical Simulation of a Boron Loaded Gel Fuel Ramjet Combustor DESCRIPTION:Lecturer:David Diskin\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The ramjet is an air-breathing propulsion engine\, which r elies on the ram effect for compressing the entering air\, thus\, eliminat ing the need for a compressor. Ramjets have no moving parts\, the entering air is compressed aerodynamically is mixed with the fuel and ignited. Fin ally\, the burned gases accelerate in a converging-diverging nozzle genera ting thrust.\nIn the present research\, the ramjet engine fuel is kerosene gel in which boron particles have been added. Boron has 140% energy per u nit mass in comparison to hydrocarbon fuels and 300% energy per unit volum e. Gelled kerosene provides the means that contain the boron powder and pr events particle sedimentation.\nAn early study of Hadad et al. showed the high performance potential of a boron loaded ramjet engine with specific i mpulse higher than 2\,000 s. The scope of the present study is to evaluate the performance of a ramjet loaded with boron and to investigate the effe ct of the various parameters\, such as bypass ratio and boron content. The study uses a commercial numerical CFD solver (FLUENT) to simulate a 3D co mbustion chamber of a ramjet with an aft burner in which bypass air is inj ected.\nBoron ignition and combustion has been modelled using King’s mod el. The model divides the combustion of the boron into two stages. Initial ly\, the boron particles are covered by a boron-oxide thin layer that prev ents from ambient oxygen to reach the boron core and react. After the remo val of the boron oxide layer\, combustion begins releasing the chemical en ergy of the boron particles.\nThe simulation of the boron combustion is ti me dependent and deals with the particle phase separately from the CFD sim ulation. In each time step the diameter of the boron particles and the hea t release are calculated. The particle distribution is polydisperse and th e particles are injected into the flowfield together with the gel fuel.\nT he results include the temperature\, velocity and particle distribution fl owfield and eventually the performance of the ramjet is derived. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-395@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180312T163000 DTEND;TZID=Asia/Jerusalem:20180312T173000 DTSTAMP:20230527T141114Z URL:https://aerospace.technion.ac.il/events/the-hanin-prize-seminar-harnes sing-unsteady-forces-to-achieve-powerful-propulsion/ SUMMARY:The Hanin Prize Seminar - Harnessing Unsteady Forces to Achieve Pow erful Propulsion DESCRIPTION:Lecturer:Prof. Ephraim (Effie) Gutmark\n Faculty:Department of Aerospace Engineering and Engineering Mechanics\n Institute:University of Cincinnati\n Location:Classroom 165\, ground floor\, Library\, Aerospace E ng.\n Zoom: \n Abstract: \n Details: \n Propulsion and combustion scientis ts and engineers have been fighting combustion instabilities in solid and liquid rockets and in air-breathing propulsion systems for many decades.  This has been recognized as one of the most severe hindrances to the dev elopment of these engines because the unsteady pressure forces that are am plified under these conditions can result in destruction of the engine.    Engines are designed with various control strategies to keep pressure p ulsations from reaching excessive levels and often their operation boundar ies are set to avoid entering these dangerous zones.   More recently\, i nterest has been growing in the propulsion community in developing engines that\, by design\, operate in an unsteady manner.  These types of engine s are based on concepts such as pressure gain combustion or constant volum e combustion.  Though not new\, these technologies have the potential to significantly increase the propulsive efficiency. This seminar will propos e an interesting possible link between the new insight gained from recent research in the latter topic to the older problem of combustion instabilit ies. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-28@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180314T090000 DTEND;TZID=Asia/Jerusalem:20180314T100000 DTSTAMP:20221030T083437Z URL:https://aerospace.technion.ac.il/events/the-58th-israel-annual-confere nce-on-aerospace-sciences-iacas/ SUMMARY:The 58th Israel Annual Conference on Aerospace Sciences (IACAS) DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Dan Panorama H otel Tel Aviv & Technion\, Haifa\n Zoom: \n Abstract: \n Details: The 58th IACAS  will take place on:\nMarch 14\, 2018 – Dan Panorama Hotel\, Tel Aviv\, Israel\nMarch 15\, 2018 – Technion Campus\, Haifa\, Israel\nThe Israel Annual Conference on Aerospace Sciences\, spanning several generati ons\, is an important annual event on the calendar of the aerospace comm unity in Israel and arouses a great deal of interest abroad. Taking part i n this yearly event are engineers\, scientists and experts in the field of aeronautics and astronautics\, representing well-known local aerospace agencies and industries\, as well as participants from major research ce nters worldwide.\nThe two day conference covers new research\, presents up -to-date technology and provides a forum for exchanging new ideas.\n CATEGORIES:Events LOCATION:Dan Panorama Hotel Tel Aviv & Technion\, Haifa END:VEVENT BEGIN:VEVENT UID:0-403@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180319T163000 DTEND;TZID=Asia/Jerusalem:20180319T173000 DTSTAMP:20230530T180414Z URL:https://aerospace.technion.ac.il/events/approaches-for-the-monitoring- of-airfoil-aerodynamic-noise/ SUMMARY:Approaches for the Monitoring of Airfoil Aerodynamic Noise DESCRIPTION:Lecturer:Michael Weidenfeld\n Faculty:Department of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abs tract: \n Details: \n Airfoil noise is a dominant component in the acousti c signature of a wide variety of aerodynamic systems. In line with current interest in reducing aircraft noise\, the present work studies means by w hich airfoil aerodynamic sound may be monitored. The principal approach ad opted is motivated by biomimetic observations of the quiet flight of owls. Subsequently\, we investigate the effects of airfoil porosity\, elasticit y and non-homogeneity on the acoustic far field of a two-dimensional airfo il set at low Mach and high Reynolds number flow. Applying the Powell-Howe acoustic analogy\, the system near-field description is obtained using th in-airfoil methodology\, and then substituted as a source term in the vort ex sound equation. The leading order airfoil dipole-type signature is eval uated\, and conditions for sound reduction and amplification are found. Th e limit case of a thin airfoil having vanishing bending rigidity is examin ed in detail\, to rationalize the impact of material flexural stiffness on the system near and far fields.\nIn a secondary effort\, the broad-band a erodynamic noise of a NACA0012 airfoil is investigated using high-fidelity Large Eddy Simulations (LES). The obtained noise sources are projected to the far field using the Ffowcs Williams-Hawkings acoustic analogy. Both n ear- and far-field results are validated\, followed by preliminary investi gation of the effects of trailing-edge temperature variations on the syste m acoustic radiation. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-25@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180321T123000 DTEND;TZID=Asia/Jerusalem:20180321T133000 DTSTAMP:20221030T083438Z URL:https://aerospace.technion.ac.il/events/the-facultys-2nd-annual-concer t/ SUMMARY:The Faculty’s 2nd Annual Concert DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty of Aer ospace Engineering\, Auditorium 235\n Zoom: \n Abstract: \n Details: The F aculty’s 2nd annual concert will take place on Wednesday\, March 21st\, at 12:30\, in Auditorium 235.\n\nAll Aerospace Engineering faculty member s\, students and employees are most invited to take part — preferably an active one!\n\nA piano will be available for participants’ use.\n\nFor details please contact Asst. Prof. Avshalom Manela at amanela@technion.ac .il\n CATEGORIES:Events LOCATION:Faculty of Aerospace Engineering\, Auditorium 235 END:VEVENT BEGIN:VEVENT UID:0-402@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180321T163000 DTEND;TZID=Asia/Jerusalem:20180321T173000 DTSTAMP:20230530T180409Z URL:https://aerospace.technion.ac.il/events/enhancing-the-performance-of-s oft-materials-a-guide-for-micro-structural-design/ SUMMARY:Enhancing the Performance of Soft Materials: A Guide for Micro-Stru ctural Design DESCRIPTION:Lecturer:Dr. Noy Cohen\n Faculty:Mechanical Engineering Departm ent and Materials Department\n Institute:University of California\, Santa Barbara\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng. \n Zoom: \n Abstract: \n Details: \n Following a short overview of my rece nt work on the modelling of the electromechanical response of liquid metal embedded elastomers and the non-linear behavior of cellular materials\, t his seminar will focus on the coupled electro-mechanical response of diele ctric elastomers (DEs). DEs are materials capable of undergoing large defo rmations in response to electric excitation. These dielectrics can be empl oyed in a wide variety of applications\, such as sensors\, actuators\, and energy harvesting devices. Currently\, the functionality of these materia ls is limited due to the high electric fields required to obtain meaningfu l deformations.\nTo overcome this obstacle\, a better understanding of the influence of the micro-structural constituents on the overall behavior is required. To this end\, I present a rigorous multi-scale entropy-based an alysis that begins with a single dipolar monomer and accounts for the phys ical structure of a polymer chain through statistical considerations. By e mploying the laws of thermodynamics and variational formulations\, the mac roscopic response of a polymer network subjected to a coupled electro-mech anical loading is determined.  The merit of the proposed model is demonst rated through a comparison with several experimental findings. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-40@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180328T163000 DTEND;TZID=Asia/Jerusalem:20180328T173000 DTSTAMP:20221030T083439Z URL:https://aerospace.technion.ac.il/events/the-5th-annual-professor-singe r-memorial-lecture-an-afternoon-talk-on-bones-doctors-and-high-order-finit e-element-methods/ SUMMARY:The 5th Annual Professor Singer Memorial Lecture - An Afternoon Tal k on Bones\, Doctors and High Order Finite Element Methods DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Classroom 165\ , ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: .For a PDF version of the poster\, click here\n CATEGORIES:Events LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-397@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180409T163000 DTEND;TZID=Asia/Jerusalem:20180409T173000 DTSTAMP:20230527T141149Z URL:https://aerospace.technion.ac.il/events/solution-of-singular-different ial-games-by-gradient-methods/ SUMMARY:Solution of Singular Differential Games by Gradient Methods DESCRIPTION:Lecturer:Oleg Kelis\n Faculty:Department of Mathematics\n Insti tute:University of Haifa\n Location:Classroom 165\, ground floor\, Library \, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In this study we foc us on a zero-sum linear-quadratic differential game. One of the main feat ures of such a game is that the weight matrix of the minimizer’s control cost in the cost functional is singular. Due to this singularity\, the g ame cannot be solved either by applying the Isaacs Min-Max principle\, [1 ]\, or the Bellman-Isaacs equation approach\, [2]. In [3] such a game was analyzed with so-called regularization approach in the case where the wei ghting matrix of the minimizer’s control cost equals zero. In [4]\, the  game was studied and analyzed in which the weight matrix of the minimi zer’s control cost has appropriate diagonal singular form also using t he regularization approach. In the present work we introduce a slightly mo re general case of the weight matrix of the minimizer’s control cost th an in [4]. This means that only a part of coordinates of the minimizer’ s control is singular\, while the rest of coordinates are regular. As app lication we introduce a pursuit-evasion differential game and we propose two gradient methods\, the Arrow-Hurwicz-Uzawa and the Korpelevich method s\, for solving this game. We present numerical illustrations demonstrati ng the iterative procedures performances.\n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-404@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180411T163000 DTEND;TZID=Asia/Jerusalem:20180411T173000 DTSTAMP:20230530T180420Z URL:https://aerospace.technion.ac.il/events/manipulating-elastic-wave-prop agation-in-non-linear-flexible-materials-via-external-stimuli/ SUMMARY:Manipulating Elastic Wave Propagation in Non-Linear Flexible Materi als via External Stimuli DESCRIPTION:Lecturer:Pavel Galich\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Ranging from the aerospace to the health industries\, unde rstanding of wave propagation phenomenon in solids is pivotal to a large n umber of practical applications\, e.g.\, reduction or elimination of undes irable noise and vibrations in aerospace structures\, nondestructive mater ial testing\, or noninvasive medical diagnostic procedures. Although wave propagation in continuum media has been investigated extensively in past d ecades\, there is still a big venue for research. For example\, the abilit y of flexible materials to sustain large deformations opens rich prospects for manipulating elastic wave characteristics by deformation. Moreover\, elastic waves can be tuned through designing micro- or macro-structures\, which can be further actively controlled by external stimuli\, such as mec hanical loading\, electric or magnetic fields. However\, before switching to complex architectured materials undergoing large deformations\, we firs t need to understand how large deformations affect relatively simple isotr opic and more complex anisotropic materials.\nIn this talk\, we will start with the discussion of the acoustic properties of the relatively simple i nitially isotropic non-linear materials and proceed with the periodic laye red and fiber composites made of these materials. Firstly\, we will elabor ate on the influence of the deformation induced stiffening (intrinsic feat ure of most soft materials) on the propagation of small-amplitude elastic plane waves. Secondly\, we will illustrate that electroelastic isotropic m aterials (i.e. dielectric elastomers) can be utilized to achieve acoustic functionalities such as decoupling of pressure and shear waves by applicat ion of an electric field. Thirdly\, we will analyse wave propagation in no n-linear elastic and electroelastic laminates. In particular\, we will pre sent the long wave estimates of the phase and group velocities for the wav es propagating in the laminates subject to external mechanical or electric al stimuli. Moreover\, we will introduce the material compositions and loa ding conditions producing wide complete band gaps (frequency ranges where neither pressure nor shear waves can propagate) at low frequency ranges. F inally\, we will discuss the anisotropy of elastic wave propagation in fin itely deformed fiber composites (FCs) of different periodicity. Specifical ly\, we will investigate the influence of fiber arrangements on shear wave propagation in these FCs. Additionally\, we will show how shear waves pro pagating along fibers relate to the elastic instabilities in FCs and revea l how fiber periodicity influences elastic instabilities in FCs. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-398@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180416T163000 DTEND;TZID=Asia/Jerusalem:20180416T163000 DTSTAMP:20230530T175521Z URL:https://aerospace.technion.ac.il/events/multi-output-autoregressive-ae roelastic-system-identification-and-flutter-prediction/ SUMMARY:Multi-Output Autoregressive Aeroelastic System Identification and F lutter Prediction DESCRIPTION:Lecturer:Matan Argaman\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Flutter analysis in the production environment is typical ly based on linear models\, where the structure is modeled via a finite-el ement model\, and the aerodynamics via a linear panel code. The main defic iency of linear panel codes is their inability to estimate the unsteady ae rodynamic forces accurately\, and consequently the flutter onset\, in the transonic regime. Computational Fluid Dynamics (CFD) codes can accurately predict the flow field about complex\, realistic configurations in all fli ght regimes\, but a direct transient-response simulation is computationall y expensive and therefore not a valid tool for flutter prediction.\n\nThe current study presents CFD-based flutter prediction methodology via reduce d-order modeling of the aeroelastic system. The aeroelastic system is mode led as a Multi-Output Autoregressive process\, and the model parameters ar e identified based on aeroelastic responses simulated in a CFD code. The a eroelastic system is identified at a few sub-critical (pre-flutter) dynami c pressure values. Flutter onset is then determined from stability paramet ers that are computed for the two dominant aeroelastic modes. The methodol ogy is demonstrated on three test cases - a linear 2D airfoil\, transonic 2D flutter with reference wind tunnel test data\, and a generic transport aircraft model. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-405@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180423T163000 DTEND;TZID=Asia/Jerusalem:20180423T173000 DTSTAMP:20230530T180425Z URL:https://aerospace.technion.ac.il/events/performance-improvement-of-bou ndary-layer-ingesting-inlets-using-active-flow-control-techniques-computat ional-analysis/ SUMMARY:Performance Improvement of Boundary Layer Ingesting Inlets Using Ac tive Flow Control Techniques (Computational Analysis) DESCRIPTION:Lecturer:Irena Rudin\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In recent years\, revolutionary technologies of inlet desig n were developed in response to environmental concerns such as reduction o f noise and pollution. Part of these efforts are directed towards reductio n of overall weight and drag of air vehicles. BLI (boundary layer ingestin g) serpentine integrated inlets\, with high curvature are a critical compo nent of this design trend and very attractive for weight and drag reductio n. However\, they suffer of the disadvantage of thick boundary layer inges ted into the inlet coupled with S–shaped offset that induce losses of to tal pressure and flow uniformity inside the inlet.\nThe current study disp lays control authority over flow non-uniformity using several active flow control methods\, such as suction and blowing. The analysis is performed u sing RANS and URANS simulations. The focus is on applying active flow–co ntrol method on a BLI inlet in order to restructure the flow inside the in let and to improve engine fan–face distortion levels. First\, a baseline case\, without any flow control was calculated and compared to previously published experimental and computational results. The results of the base line calculation were used to determine the flow mechanisms that character ize the formation of flow distortion inside the inlet. Based on these resu lts\, desirable positions of suction slots could be determined in various combinations. However\, to achieve significant decrease in flow distortion \, non-neglectable mass flow was required for the suction. Therefore\, com binations of steady suction and steady/oscillatory blowing were examined. Using this AFC approach\, a significant improvement in pressure recovery a nd flow uniformity was demonstrated\, at a negligible loss in the mass flo w rate. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-386@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180430T163000 DTEND;TZID=Asia/Jerusalem:20180430T173000 DTSTAMP:20230527T140826Z URL:https://aerospace.technion.ac.il/events/start-up-stories-lecture-1-gel -propulsion-to-space-and-beyond-newrocket/ SUMMARY:Start-Up Stories\, Lecture #1 - "Gel Propulsion – To Space and Be yond" - NewRocket DESCRIPTION:Lecturer:Moti Elyashiv\n Faculty:\n Institute:NewRocket\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abs tract: \n Details: \n Founded in 2014\, NewRocket is a Technion spin-off d eveloping rocket engines for the space and aviation markets. The company c ore technology is based on decades of research activities conducted in the Fine Rocket Propulsion Center under the leadership of Prof. Benny Natan.\ n\nThe lecture will focus on the company's innovative applications for spa ce and other markets and will provide some insights of the business journe y of a unique aerospace start-up. The lecture will include a brief technic al introduction covering rocket propulsion and gel propulsion basics.\n\n\ n\n \; CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-383@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180502T163000 DTEND;TZID=Asia/Jerusalem:20180502T173000 DTSTAMP:20230527T140734Z URL:https://aerospace.technion.ac.il/events/continuous-closed-loop-transon ic-linear-cascade-for-aero-thermal-performance-studies-in-micro-turbomachi nery/ SUMMARY:Continuous Closed-Loop Transonic Linear Cascade for Aero-Thermal Pe rformance Studies in Micro-Turbomachinery DESCRIPTION:Lecturer:Eli Yakirevich\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n The present work summarizes the design process of a new continuous closed-loop hot transonic linear cascade. The facility features fully modular design which is intended to serve as a test bench for axial micro-turbomachinery components in independently varying Mach and Reynold s numbers ranges of 0 - 1.3 and 2⋅104 - 6⋅105 respectively. Moreover\, for preserving heat transfer characteristics of the hot gas section\, the gas to solid temperature ratio (up to 2) is retained. This operational en vironment has not been sufficiently addressed in prior art\, although it i s critical for the future development of ultra-efficient high power or thr ust devices.\nIn order to alleviate the dimension specific challenges asso ciated with micro-turbomachinery\, the facility is designed in a highly ve rsatile manner\, and can easily accommodate different geometric configurat ions (pitch\, ±20° stagger angle\, ±20° incidence angle)\, absent of a ny alterations to the test section. Owing to the quick swap design\, the v ane geometry can be easily replaced without manufacturing or re-assembly o f other components. Flow periodicity is achieved by the inlet boundary lay er suction and independently adjustable tailboard mechanisms. Enabling tes t-aided design capability for micro gas turbine manufacturers\, aero-therm al performance of various advanced geometries can be assessed in engine re levant environments. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-385@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180507T163000 DTEND;TZID=Asia/Jerusalem:20180507T173000 DTSTAMP:20230527T140810Z URL:https://aerospace.technion.ac.il/events/apparatus-and-experiments-for- thermal-conductivity-study-of-ablative-materials/ SUMMARY:Apparatus and Experiments for Thermal Conductivity Study of Ablat ive Materials DESCRIPTION:Lecturer:Ramin Shilav\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Research on performance of thermal protection systems is s ignificant for the development of products for aerospace applications\, su ch as internal insulation for solid rocket motors\, nozzles\, and external thermal protection insulation. Ablative materials are used as sacrificial material against the combination of high temperatures and high heat flux to the protected vessel. The unique chemical and physical characteristics of these materials face successfully the thermo-chemical ablation and mech anical erosion of the surface. Variation of thermal conductivity with temp erature cannot be predicted\, and there is a need to determine it experime ntally. Since most reactions which influence the thermal conductivity of t he ablative material occur up to a temperature of 1200K\, it was decided t o develop such an apparatus.\nIn the present work\, the development of a t hermal conductivity apparatus for research of ablative materials is presen ted. Derivation of a semi-empirical model for determining the instantaneou s thermal conductivity of the ablative material has been implemented succe ssfully. Verification testing of the apparatus was carried out in order to determine the accuracy and sensitivity of results. Four compositions of E PDM-based insulation in addition to PTFE as a reference material were test ed. Results were compared to relevant results from the literature and to a well-established apparatus\, revealing good agreement. It was found that it is possible to determining the specific heat as well as the thermal dif fusivity of the ablative material\, once the temperature dependent density is experimentally determined. The conducted experiments revealed the infl uence of the following parameters on the temperature dependent thermal con ductivity: Curing agent of the ablative material\, reinforcing fibers and fire retardant agents. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-21@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180508T173000 DTEND;TZID=Asia/Jerusalem:20180508T183000 DTSTAMP:20221030T083440Z URL:https://aerospace.technion.ac.il/events/gvahim-excellence-program-cere mony-4/ SUMMARY:“Gvahim” Excellence Program Ceremony DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Engi neering Library Classroom (no. 165)\n Zoom: \n Abstract: \n Details: Schol arships and certificates for the students of “Gvahim” Excellence Progr am\, for the 2016-2017 academic year.\nInvited: The Program’s students a nd their families\, Faculty members\, B.Sc. students and colleagues from t he Aerospace Industry .\nFor registration\, please see:\n\n\n CATEGORIES:Events LOCATION:Aerospace Engineering Library Classroom (no. 165) END:VEVENT BEGIN:VEVENT UID:0-387@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180509T163000 DTEND;TZID=Asia/Jerusalem:20180509T173000 DTSTAMP:20230527T140844Z URL:https://aerospace.technion.ac.il/events/hydrodynamic-lift-generation-b y-anguilliform-swimmers/ SUMMARY:Hydrodynamic Lift Generation by Anguilliform Swimmers DESCRIPTION:Lecturer:Alexander Rashkovsky\n Faculty:Department of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Loc ation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n A bstract: \n Details: \n Sea snakes are air-breathing aquatic animals. They have lungs. When diving\, the volume of their lungs changes with depth\, making them non-neutrally buoyant at least for a part of the dive. Gravity -buoyancy imbalance has to be compensated by hydrodynamic means. Moreover\ , the center of buoyancy (xb) and the center of mass (xcm) may not coincid e\, and in this case the resulting couple has to be compensated by hydrody namic means as well.\n\nSimilar to many other elongated swimmers\, sea sna kes propel themselves by lateral deformation waves propagating along their bodies (nose to tail) faster than they swim. As opposed to other elongate d swimmers\, sea snakes also twist their tails in coordination with the la teral wave. This study attempts to quantify the hydrodynamic lift and coup le this type of propulsion can generate\, utilizing the framework of elong ated body theory originally developed by J. Lighthill.\n\nThe quantitative results are validated through the existing data of buoyancy states sea sn akes can swim at\, which appear to fit. The values of hydrodynamic couple cannot be validated due to absence of relevant data\, however they appear to be too small. Additional methods of dealing with excessive pitching mom ent are proposed.\n\n.\n\n. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-388@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180514T163000 DTEND;TZID=Asia/Jerusalem:20180514T173000 DTSTAMP:20230527T140903Z URL:https://aerospace.technion.ac.il/events/start-up-stories-lecture-2-a-m ethodological-process-to-optimize-capturing-updrafts-in-non-motorized-air- vehicles-falco-technologies/ SUMMARY:Start-Up Stories\, Lecture #2: "A Methodological Process to Optimiz e Capturing Updrafts in Non-Motorized Air Vehicles" - Falco Technologies DESCRIPTION:Lecturer:Teddy Gilaad\n Faculty:\n Institute:Falco Technologies \n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom : \n Abstract: \n Details: \n In the traditional non-motorized aerial vehi cles (Paragliders\, sailplanes and hang gliders) world\, pilots use a “V ariometer” tool to identify that they are in an updraft (such as hot air thermal)\, to start maneuvers to stay within the just found updraft\, in order to gain maximum height possible. It is a highly intellectual and int uitive process that requires long study\, long experience and stubbornness \, in order to stay aloft. This talk will describe a process which is a pa tent pending invention\, to make it into a more methodological and simple process for the pilot to follow.\n\nSince it became a methodological and simple process\, it enables converting the methodology into a computer pr ogram and build upon it the “Autonomous Glider” that may stay aloft fo r a day or more\, a really huge\, great and new marketplace.\n\n\n\n \ ; CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-374@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180521T160000 DTEND;TZID=Asia/Jerusalem:20180521T170000 DTSTAMP:20230527T140250Z URL:https://aerospace.technion.ac.il/events/start-up-stories-lecture-3-rev olutionizing-satellite-communication-by-using-expandable-antennas-nslcomm/ SUMMARY:Start-Up Stories\, Lecture #3: "Revolutionizing Satellite Communica tion by Using Expandable Antennas" - NSLComm DESCRIPTION:Lecturer:Dr. Raz Itzhaki\n Faculty:\n Institute:NSLComm\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abs tract: \n Details: \n By changing the norm for Geostationary (GEO) and Low er Earth Orbit (LEO) satellite manufacturers’ antenna fabrication techno logy\, incorporating NSLComm’s transformational product will increase ba ndwidth on NanoSats and GEOs by a factor of ten (for GEO) and one hundred for (LEO) while providing a cost-effective and rocket-storage optimized so lution.\n\nNSLComm (NSL) provides satellite manufacturers with unprecedent ed large aperture expandable antennas for satellite communications. With a dvancements such as designing and incorporating an adaptive corrective and pattern shaping sub-reflector and shape memory polymer reflectors\, NSL c reates lightweight expandable antennas. These are of a compact volume when stowed during launch\, permit for continual beam control and shaping and provide very high throughput satellite (VHTS) bandwidth performance.  Key benefits include higher bandwidth and power for extremely fast internet\, Ultra High Def (4K) video support\, in-flight connectivity\, LEO to GEO c omms\, and more. NSL solution provides a lower price per bit to the end-us er and market growth for the provider.\n\n\n. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-384@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180523T163000 DTEND;TZID=Asia/Jerusalem:20180523T173000 DTSTAMP:20230527T140749Z URL:https://aerospace.technion.ac.il/events/development-of-kw-scale-orc-po wer-systems-opportunities-and-challenges/ SUMMARY:Development of kW-scale Organic Rankine Cycle Power Systems: Opport unities and Challenges DESCRIPTION:Lecturer:Prof. Vincent Lemort\n Faculty:Thermodynamics Laborato ry\n Institute:University of Liège\, Belgium\n Location:Classroom 165\, g round floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n This seminar will summarize the outcomes of the different research projec ts dealing with kW-scale ORC (Organic Rankine Cycle) power systems that ha ve been conducted for more than 10 years at the University of Liège.\nThe experience gained with the different experimental studies will be discuss ed. These studies covered the characterization of prototypes of volumetric expanders (scroll\, screw\, piston\, roots)\, turbines (radial inflow\, a xial)\, heat exchangers and pumps\, as well as the comparison of performan ce achieved with several working fluids (including organic fluids and wate r). Specific experimental techniques and their use in the process of model calibration will be presented. Among these techniques\, the measurement o f the charge division among components will be highlighted.\nThe developme nt\, in different simulation platforms\, and the experimental validation o f steady-state and dynamic simulation models will be presented. The use of these models for the design optimization of components and systems\, for the investigation of advanced control strategies and for the comparison of innovative architectures\, will be highlighted. Advanced control strategi es (including Model Predictive control and advanced PID) are particularity suitable to ORC coupled to highly transient heat sources. Innovative arch itectures include trilateral and super-critical cycles better adapted to s ome heat sources. Finally\, special applications of ORCs\, such as waste h eat recovery from internal combustion engines\, CHP and pumped thermal ene rgy storage\, will be presented. For all these applications\, opportunitie s and challenges will be listed and discussed. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-379@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180530T163000 DTEND;TZID=Asia/Jerusalem:20180530T173000 DTSTAMP:20230527T140626Z URL:https://aerospace.technion.ac.il/events/turbulence-droplets-and-the-st ability-of-reacting-flows/ SUMMARY:Turbulence\, Droplets and the Stability of Reacting Flows DESCRIPTION:Lecturer:Yuval Dagan\n Faculty:Department of Mechanical Enginee ring\n Institute:Massachusetts Institute of Technology – MIT\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n The interaction between turbulence\, chemical kinetics a nd droplet dynamics plays an important role in reacting flows and can lead to instability. Understanding the underlying mechanisms that drive these processes is critical for predicting and controlling them\, and may signif icantly enhance combustion efficiency which is a crucial design parameter for gas-turbines and propulsion systems.\nIn this talk\, I will present re sults from theoretical and experimental studies of different reacting flow configurations. Employing large eddy simulations\, we show that under lea n premixed conditions the dynamic response of a turbulent reactive flow is strongly impacted by the fuel chemistry. In order to gain insight into so me of the underlying mechanisms we formulate a new linear stability model that incorporates the impact of finite rate chemistry on the hydrodynamic stability of shear flows. In contrast to previous studies which typically assume that the velocity field is independent of the kinetic rates\, tempe rature coupled mechanisms are accounted for through a variable density Nav ier-Stokes formulation. This formulation is shown to agree with results of our recent experimental and computational studies and suggests a physical explanation for the observed impact of finite rate chemistry on turbulent shear flow instability.\nAdding particles and droplets to the reactive fl ow may alter its structure and stability. I will revisit Saffman’s semin al work on the stability of particle-laden flows\, and present a new conce pt for the analysis of hydrodynamic stability of multiphase flows using th e sectional approach. Preliminary results reveal the impact of droplet eva poration on the stability of the Hagen-Poiseuille flow. Remarkably\, while the addition of non-evaporating particles tends to stabilize the flow\, v olatile droplets of the same size can destabilize the flow. This may also imply an earlier transition to turbulence in flows advecting volatile drop lets. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-377@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180606T163000 DTEND;TZID=Asia/Jerusalem:20180606T173000 DTSTAMP:20230527T140427Z URL:https://aerospace.technion.ac.il/events/start-up-stories-lecture-4-win dproof-vtol-aircraft-colugo-systems/ SUMMARY:Start-Up Stories\, Lecture #4: “Windproof VTOL Aircraft" - Colugo Systems DESCRIPTION:Lecturer:Amit Regev\n Faculty:\n Institute:Colugo Systems\n Loc ation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n A bstract: \n Details: \n Since the dawn of aviation there have been many at tempts to build fixed-wing aircraft that take off and land vertically\, ca lled VTOLS. These aircraft solve the need for the use of runways\, which c reate significant logistical bottlenecks in aircraft traffic\, and  affec t the ability to reach the target point accurately and quickly.\nOf all th ese aircraft developed\, only four have been mass produced. All of these a re military and suffer from high maintenance costs\, limited take off abil ity in windy conditions\, and low reliability.\nColugo has developed an ai rcraft that provides a solution to these problems.\n\n. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-376@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180613T163000 DTEND;TZID=Asia/Jerusalem:20180613T173000 DTSTAMP:20230527T140407Z URL:https://aerospace.technion.ac.il/events/an-investigation-of-wing-elast icity-effects-on-store-separation/ SUMMARY:An Investigation of Wing Elasticity Effects on Store Separation DESCRIPTION:Lecturer:Itzik Mizrahi\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n The study explores wing elasticity effects on the store s eparation process\, based on computational fluid dynamics simulations. The nominal test case is that of an unmanned aerial vehicle that carries two identical stores\, without fins or control surfaces\, on two wing stations in a symmetric configuration. The stores are ejected during straight and level flight at 0.35M\, 2500m.\nSimultaneous\, time-accurate analysis of t he dynamic aeroelastic wing response and the store's trajectory reveals th at the most significant aeroelastic effect is a roll motion developed by t he store. This roll motion is due to misalignment of the ejection force ve ctor and the store's center of gravity\, due to the wing's static and dyna mic elastic deformations.\nThe seminar talk will present a parametric stud y of the effects of various structural and configurational parameters on t he wing's response\, and consequently on the store's rolling motion. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-380@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180618T163000 DTEND;TZID=Asia/Jerusalem:20180618T173000 DTSTAMP:20230527T140644Z URL:https://aerospace.technion.ac.il/events/start-up-stories-lecture-6-dev elopment-of-a-new-rotor-with-efficiency-up-to-4-times-higher-than-conventi onal-rotors-and-a-significantly-lower-noise-level-optivector/ SUMMARY:Start-Up Stories\, Lecture #5: “Development of a New Rotor with E fficiency up to 4 Times Higher than Conventional Rotors and a Significantl y Lower Noise Level" - OptiVector DESCRIPTION:Lecturer:\n Faculty:\n Institute:Optivector\n Location:Classroo m 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n De tails: \n The presentation will describe the limitations of current rotors \, explain why several countries have recently started to work again on th e cycloidal rotor\, a technology invented 80 years ago\, and present OptiV ector’s revision of the cycloidal rotor concept in order to achieve unpr ecedented lift force and limited noise. The presentation will then describ e the market potential and some major applications.\n\n\n\n.\n\n \; CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-373@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180620T163000 DTEND;TZID=Asia/Jerusalem:20180620T173000 DTSTAMP:20230527T140230Z URL:https://aerospace.technion.ac.il/events/start-up-stories-lecture-6-bei ng-a-drone-market-enabler-parazero/ SUMMARY:Start-Up Stories\, Lecture #6: “Being a Drone Market Enabler" - P araZero DESCRIPTION:Lecturer:Eyal Regev\n Faculty:\n Institute:PARAZERO Drone Safet y Systems\n Location:Classroom 165\, ground floor\, Library\, Aerospace En g.\n Zoom: \n Abstract: \n Details: \n Managing the Triangle: Technology\, Regulations and the Market of commercial drones.\n\nNew breakthroughs in safety measures that enabled new air traffic regulations\, which pave the path to a multi-billion dollar market and a revolutionary change in the w orld of trade and commerce.\n\n\n\n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-375@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180625T120000 DTEND;TZID=Asia/Jerusalem:20180625T130000 DTSTAMP:20230527T140317Z URL:https://aerospace.technion.ac.il/events/the-2018-phd-seminar-in-memory -of-prof-shmuel-and-mrs-noemi-merhav-silence-is-golden/ SUMMARY:The 2018 PhD Seminar in Memory of Prof. Shmuel and Mrs. Noemi Merha v - "Silence is Golden" DESCRIPTION:Lecturer:Shimon Julius\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n In this talk\, we will explore the concept and physics of Thermphone sound production. Thermophone transducers produce sound by est ablishing a periodic heat flux into a fluid medium. This heat flux signal engenders a corresponding periodic local pressure rise\, in a physically s tatic process.\nPressure field stimulation and sound production via Joule heating has been studied since the late 19th century\, though modern capab ilities in material science have recently thrust the technology anew into the spotlight due to dramatic improvements in potential device efficiency. Furthermore\, it has become apparent that though the physics of sound pro duction and propagation is well understood\, the heat transfer mechanisms within the transducers themselves is not well understood. At the temporal and length scales inherent to the operation of these devices\, we have unc overed evidence of non-Fourier heat conduction phenomena\, such as ballist ic and wavelike energy transport processes.\nAs well as a discussion of th e theoretical aspects thermophone sound generation\, we demonstrate our re search into a novel type of sound cancellation approach that takes advanta ge of the unique properties of thermophone transducers to perform sound ca ncellation on the source boundary itself. Finally\, we will touch on the i mplications of this technology for the aerospace industry. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-378@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180625T163000 DTEND;TZID=Asia/Jerusalem:20180625T173000 DTSTAMP:20230527T140451Z URL:https://aerospace.technion.ac.il/events/generalized-equilibrium-flow-i n-a-shear-driven-open-microchannel/ SUMMARY:Generalized Equilibrium Flow in a Shear-Driven\, Open Microchannel DESCRIPTION:Lecturer:Lilach Mazor\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Micropatterned materials are important in the construction of superhydrophobic surfaces for drag reduction and protective coatings. A new generation of these materials incorporates a layer of immiscible flu id into the surface pattern to enhance or customize the surface mechanical behavior. When such liquid-infused surfaces are exposed to an external sh ear flow\, there is a risk of losing the infused liquid\, and thus designi ng surface structures capable of retaining fluid under shear becomes impor tant.\nIn this work\, theoretical calculations and experiments will be pre sented to describe the steady-state fluid retention in an open microfluidi c channel under shear\, as a function of the streamwise geometry of the ch annel. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-31@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180627T160000 DTEND;TZID=Asia/Jerusalem:20180627T190000 DTSTAMP:20221030T083441Z URL:https://aerospace.technion.ac.il/events/conclusion-and-presentation-of -the-undergraduate-students-final-design-projects-2017-18/ SUMMARY:Conclusion and Presentation of the Undergraduate Students' Final De sign Projects 2017/18 DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:The Faculty of Aerospace Engineering\n Zoom: \n Abstract: \n Details: \n CATEGORIES:Events LOCATION:The Faculty of Aerospace Engineering END:VEVENT BEGIN:VEVENT UID:0-370@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180709T133000 DTEND;TZID=Asia/Jerusalem:20180709T143000 DTSTAMP:20230527T135921Z URL:https://aerospace.technion.ac.il/events/guest-asri-seminar-two-phase-a veraging-of-optimal-control-systems/ SUMMARY:Guest ASRI Seminar - "Two-Phase Averaging of Optimal Control System s" DESCRIPTION:Lecturer:Dr. Lamberto Dell’Elce\n Faculty:Team McTAO\n Instit ute:INRIA Sophia Antipolis Méditerranée\, France\n Location:ASRI Seminar Room\n Zoom: \n Abstract: \n Details: \n Averaging is a valuable techniqu e to gain understanding in the long-term evolution of dynamical systems ch aracterized by slow and fast dynamics. Recent contributions proved that av eraging can be applied to the extremal flow of optimal control problems. T he present work extends these results by tackling averaging of time optima l systems with two fast variables.\nThe first part of the talk is devoted to the justification of the application of the averaging principle to this problem. The key role of the adjoints of fast variables is then disclosed \, which yields the assessment of a compatibility condition between their boundary values in the original and averaged systems.\nThe second part is devoted to the a posteriori reconstruction of short-period variations. The classical near-identity transformation exploited in dynamical system theo ry is shown to be inadequate to restore the adjoints of slow variables bec ause of the peculiar form of their equations of motion. Hence\, a consiste nt transformation is developed. Effects due to the crossing of resonances are finally discussed. Developments are applied to a time-optimal low-thru st orbital transfer in the Earth-Moon system. CATEGORIES:Seminars LOCATION:ASRI Seminar Room END:VEVENT BEGIN:VEVENT UID:0-381@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180711T163000 DTEND;TZID=Asia/Jerusalem:20180711T173000 DTSTAMP:20230527T140701Z URL:https://aerospace.technion.ac.il/events/cooperative-object-manipulatio n-a-rigidity-theory-approach/ SUMMARY:Cooperative Object Manipulation: A Rigidity Theory Approach DESCRIPTION:Lecturer:Douglas Goldenberg\n Faculty:Department of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abs tract: \n Details: \n Moving objects with a single robot is a common pract ice\; however\, the weight and dimensions of the cargo oftentimes limit th e task. To aid this\, we propose using multiple coordinating robots to mo ve large objects. The main challenge in this approach is that the robots d o not know the center of mass\, or even the geometry\, of the object they are moving\, but do have complete information regarding their own relati ve formation. This fact motivates solving the problem using rigidity th eory\, a tool recently used in formation control. Within this context\, th e planar motion of the object can be decoupled into pure steady state tran slations and rotations by utilizing the eigenvectors of the corresponding framework’s rigidity matrix. This formulation is beneficial because it o nly requires local information to create any desired trajectory.\nThis wor k explores how applying forces computed using the rigidity matrix can be u sed to estimate the center of mass of the object\, allowing the robots to adjust the forces and therefore to follow any desired trajectory.\nFinally \, we demonstrate the analytical results with numerical simulations. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-372@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180725T163000 DTEND;TZID=Asia/Jerusalem:20180725T173000 DTSTAMP:20230527T140213Z URL:https://aerospace.technion.ac.il/events/investigation-of-abs-paraffin- based-3-d-printed-hybrid-rocket-fuels/ SUMMARY:Investigation of ABS-Paraffin Based 3-D Printed Hybrid Rocket Fuels DESCRIPTION:Lecturer:Jacob Bresler\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Chemical rocket propulsion systems can be divided into so lid\, liquid\, and hybrid propellant systems. Despite the numerous benefit s that hybrid rocket systems enjoy over both solid and liquid propellant s ystems\, their widespread implementation has not yet been achieved. This i s due to the low regression rates of classical non-liquefying hybrid fuels \, as well as the poor mechanical properties generally possessed by higher performance liquefying hybrid fuels.\nPrevious works into improving the m echanical properties of liquefying fuels\, such as paraffin\, generally we re limited to the blending of the paraffin with polyethylene\, which does provide some improvement\, but also slightly decreases the regression rate of the paraffin fuel. This research presents an investigation on the effe ct of the addition of an internal skeleton composed of ABS on the performa nce of a Paraffin/GOX hybrid propellant system.\nThe most important findin gs of this research were the significantly increased regression rate obser ved for the grains that possessed ABS structures when compared to the regr ession rate for grains composed solely of Paraffin\, this added regression rate was also accompanied by better mixing between the fuel and oxidizer\ , as well as a higher combustion efficiency. For the oxidizer fluxes studi ed the regression rates of the ABS grain was approximately .2 mm/s\, of th e pure paraffin grain about 1 mm/s whereas for the ABS-paraffin structure the regression rate reached 1.4-1.6 mm/s\, which seems to be a great impro vement. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-382@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180801T163000 DTEND;TZID=Asia/Jerusalem:20180801T173000 DTSTAMP:20230527T140717Z URL:https://aerospace.technion.ac.il/events/development-of-aerodynamic-for -the-design-of-a-wind-turbine-in-a-yawed-flow/ SUMMARY:Development of Aerodynamic Model for the Design of a Wind Turbine i n a Yawed Flow DESCRIPTION:Lecturer:Valentin Ognev\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Energy supply is the basis for the development of a mode rn society. Nowadays most of the energy supply is based on fossil fuels. N evertheless\, the use of renewable energy has increased significantly duri ng the recent years.\nWind energy is one of the important sources of renew able energy.\nHorizontal axis wind turbines (HAWT) are by far the most pop ular means of converting wind energy into electrical energy. The research on HAWT has been focused on the case of axial flow where the direction of the incoming wind is parallel to the turbine axis. Nevertheless\, wind ch anges its direction continuously and thus most of the time wind turbines w ork in yawed flow where there exists a finite angle between the turbine ax is of rotation and wind direction. Yawed results in a reduction in the ene rgy production\, but more important is the fact that it results in an unst eady behavior: Periodic aerodynamic loads that result in severe fatigue pr oblems in the various components of the turbine.\nThe aim of the present r esearch is to develop an efficient method of calculating the aerodynamic l oads that act along the wind turbine blades while it operates in yawed flo w.\nThe research consists of two main parts:\nIn the first part a new actu ator disk model for calculating the induced velocities over the disk\, is combined with a blade element model for calculating the loads along the bl ades. The new actuator disk model is capable of modeling the non-uniform c haracteristics of the flow across the disk (in the radial and circumferent ial directions) due to the yawed flow. Because of the unsteady aerodynamic characteristics of the blade cross-sectional incoming flow\, the blade-el ement model includes the influence of unsteady effects on the blade cross- sectional aerodynamic coefficients.\nin the second model the loads along t he blades are calculated again using the blade-element model. The induced velocity in the flow field is calculated after the pressure field is calcu lated by a solution of the pressure wave equation. The input to the wave e quation (Ffowcs\, Williams\, Hawking equation) are the loads along the bla des. Various numerical methods and approximations are used in order to mak e the calculations more efficient. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-363@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180806T163000 DTEND;TZID=Asia/Jerusalem:20180806T173000 DTSTAMP:20230527T135707Z URL:https://aerospace.technion.ac.il/events/noise-abatement-techniques-for -small-uav-propellers/ SUMMARY:Noise Abatement Techniques for Small UAV Propellers DESCRIPTION:Lecturer:Yonatan Maor\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Recent years have seen rapid growth in the small-unmanned air vehicles (UAV) industry. This increase in drone usage causes many disr uptions in our everyday lives\, particularly noise. Increased noise regula tions around residential and commercial areas\, and the importance of a si lent flight in military settings\, mean that the acoustic signature of dro nes is of great concern. The use of electric propulsion systems has turned the propellers into a prominent source of noise. The quietness and the ef ficiency of propulsive system are key aspects in the design of UAV. Theref ore\, the ability to understand\, predict and decrease rotor noise has bec ome a major goal for both civil and military applications.\nWithin the sco pe the study\, acoustic signature and aerodynamics performance of off-the- shelf APC Electric and in-house designed and manufactured (3D printed) pro pellers was studied in an anechoic environment. The aim of the study was n ot only understand the link between aeroacoustic and aerodynamic performan ce\, but also suggest techniques to attenuate the acoustic signature. Trea tments included the addition of surface roughness\, applied a short distan ce downstream of the propeller’s leading edge\, and application of trail ing-edge serrations. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-369@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180807T140000 DTEND;TZID=Asia/Jerusalem:20180807T150000 DTSTAMP:20230527T135858Z URL:https://aerospace.technion.ac.il/events/guest-asri-seminar-pulsar-base d-deep-space-autonomous-navigation/ SUMMARY:Guest ASRI Seminar - "Pulsar-Based Deep Space Autonomous Navigation " DESCRIPTION:Lecturer:Prof. Jason L. Speyer\n Faculty:Mechanical and Aerospa ce Engineering\n Institute:UCLA\n Location:ASRI Seminar Room (room No. 201 )\n Zoom: \n Abstract: \n Details: \n The performance of pulsar-based navi gation for deep space exploration is investigated by considering the deep space DAWN mission. The flight trajectory of the DAWN spacecraft is used i n the numerical simulation to mimic a realistic mission scenario. This sce nario accounts for clock uncertainty\, pulsar timing noise\, maneuver exec ution errors\, sequential observation and interruptions between pulsar obs ervations. Although an efficient Extended Kalman Filter (EKF) was implemen ted for most of the DAWN flight\, a particle filter was used to reduce the large initial position uncertainty in which the integer ambiguity of the number of pulsar wavelengths were resolved. The resulting position and vel ocity uncertainty initializes the EKF. In addition to numerical simulation s\, an analytical comparison between the measurement noises of X-ray based and radio based pulsar timing/navigation systems is discussed. CATEGORIES:Seminars LOCATION:ASRI Seminar Room (room No. 201) END:VEVENT BEGIN:VEVENT UID:0-367@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180808T163000 DTEND;TZID=Asia/Jerusalem:20180808T173000 DTSTAMP:20230527T135824Z URL:https://aerospace.technion.ac.il/events/the-influence-of-injectors-con figuration-on-the-quality-of-fuel-spray-during-start-up-in-jet-engines/ SUMMARY:The Influence of Injector's Configuration on the Quality of Fuel Sp ray During Start Up in Jet Engines DESCRIPTION:Lecturer:Dafna Marcovici\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n Following a configuration change of F110 engines in the IAF\, fire balls had been seen during start-up in several engines. In the new configuration several components are replaced\, including fuel nozzle s (20 similar nozzles).\nIn order to prevent the fire balls appearance\, i t was chosen to replace the new fuel nozzles with the original nozzles con figuration (16 standard nozzles and 4 pilot nozzles on both sides of the i gnitors).\nThis work included assessment of the effect of the fuel spray c haracteristics on the appearance of fire balls during engine start-up as w ell as detailed examination of the spray process in the different nozzles and its effect on the characteristics and quality of fuel spray in jet eng ines. In this work experiments were performed in order to characterize the fuel spray in each type of nozzle. In addition\, an analysis of the exper imental results was done in order to identify a link between the different fuel spray characteristics and the appearance of fire balls.\nThe experim ental results and analysis had shown that the new nozzles configuration pr ovide inferior fuel spray characteristics comparing the old nozzles. The r esults showed better diameter distribution and velocity in the original fu el nozzles. Moreover\, it was seen that the original pilot nozzle provides a "hollow cone" type of spray while the other types of nozzles provide ma ss flux mostly at the center of the spray.\nThe results showed that the or iginal nozzles configuration\, where pilot nozzles are located on both sid es of the ignitors\, provides a better fuel spray that allows for better c ombustion of the fuel droplets and as a result for better combustion of th e entire spray. Furthermore\, it was found that the fuel spray provided by the new nozzles configuration makes it harder for the combustion to consu me all the fuel in the combustion case and therefore represents\, in high probability\, a potential cause for the appearance of fire balls in the en gines.\nAdditionally\, a review was done of all other changes that were do ne in the new engine configuration and their effect on appearance of fire balls. This work has focused on the replacement of the fuel nozzles and it was found that the original configuration allows for better combustion. H owever\, it would seem that the fire balls appeared due to the combination of several changes in the engine\, Therefore\, further investigation is n eeded in order to explore the combined influence of the changes done in th e engine on the fire balls appearance. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-360@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180822T163000 DTEND;TZID=Asia/Jerusalem:20180822T173000 DTSTAMP:20230527T135618Z URL:https://aerospace.technion.ac.il/events/dynamic-response-of-an-elastic -aircraft-to-store-ejection/ SUMMARY:Dynamic Response of an Elastic Aircraft to Store Ejection DESCRIPTION:Lecturer:Daniel Kariv\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Military aircraft typically carry under-wing stores such a s bombs or external fuel tanks. During a mission\, one or more stores may be ejected with the aid of a jettison force that pushes them away from th e aircraft into a safe trajectory.  Store release changes the load balanc e on the aircraft\, causing both static and dynamic structural response o f the flexible wings\, as well as a rigid body motion of the whole aircraf t. The large ejection forces might result in excessive structural dynamic loads that must be accounted for in the structural design process. The pr oblem of ejection loads is becoming more severe for modern\, flexible air craft configurations (typically\, unmanned aircraft vehicles)\, in which s mall stores are ejected with large jettison forces. Additionally\, stores are sometimes released in ripple\, namely shortly one after another\, bef ore the dynamic response from the previous ejection has decayed completely .\n\nThe study presents a frequency-domain method for computing the struct ural dynamic response of an elastic aircraft to store ejection\, accountin g for the jettison\, the inertial\, and the unsteady aerodynamic forces.  A novel solution method is proposed\, that accounts for the time-variati on of structural properties of the configuration (following each store re lease) in the frequency domain. The study examines the physical factors th at affect the aircraft response to store ejection. The study also present s cases of ripple ejection and shows how the time-interval between ejectio ns could be optimized to reduce the loads. The methodology is demonstrate d on a test case of a subsonic elastic generic unmanned aircraft vehicle c arrying up to six stores on each wing. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-364@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20180829T163000 DTEND;TZID=Asia/Jerusalem:20180829T173000 DTSTAMP:20230527T135735Z URL:https://aerospace.technion.ac.il/events/guidance-for-rendezvous-and-do cking-with-tumbling-space-targets/ SUMMARY:Guidance for Rendezvous and Docking with Tumbling Space Targets DESCRIPTION:Lecturer:Jérémie Lejzerowicz\n Faculty:Department of Aerospac e Engineering\n Institute:Technion – Israel Institute of Technology\n Lo cation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n This research focuses on a particular case of dis tributed space systems technology: spacecraft rendezvous missions. More sp ecifically\, the case of a two-phase satellite rendezvous maneuver is exam ined for rigid bodies instead of point-masses. Traditional Clohessy-Wiltsh ire models for relative motion become invalid when the spacecraft shapes a re considered. The studied mission is considered non-cooperative\, in the sense that the target spacecraft does not maneuver to facilitate rendezvou s with the chaser spacecraft.\nThe first part of this research considers a new guidance law for rendezvous based on the well-known Proportional Navi gation guidance law\, modified for the studied mission type. The required commanded accelerations are presented in the line-of-sight reference frame (transverse and longitudinal components). Equations for the relative moti on between the target and the chaser are derived. The second part of this research discusses the estimation of the line-of-sight rate and its higher -order derivatives in the case of imperfect information due to measurement errors. Different filters are implemented\, and a performance evaluation is presented. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-366@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181010T163000 DTEND;TZID=Asia/Jerusalem:20181010T173000 DTSTAMP:20230527T135810Z URL:https://aerospace.technion.ac.il/events/wind-tunnel-study-of-the-arma- flutter/ SUMMARY:Wind-Tunnel Study of the ARMA Flutter Prediction Method DESCRIPTION:Lecturer:Tzlil Nahom Jidovetski\n Faculty:Department of Aerospa ce Engineering\n Institute:Technion – Israel Institute of Technology\n L ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Aeroelastic flutter is a destructive instabilit y phenomenon for which dedicated flight test campaigns are considered com pulsory according to airworthiness regulations. In these tests\, the dynam ic characteristics of the aeroelastic system are interpreted from measurem ents of the aircraft’s structural responses to external excitations. Ove r the years\, several flutter identification and prediction techniques h ave been suggested to increase the efficiency of flutter flight tests an d to enable better prediction of the flutter boundary. While most of the methods rely on external mechanical excitation accessories\, the Autoregre ssive Moving-Average (ARMA) flutter prediction method attempts to identif y the aeroelastic system based on the aircraft structural response to rand om air turbulence excitation.\nThis study investigates the application asp ects and the methodology of flutter prediction via ARMA system identifica tion in a dedicated wind-tunnel experiment. For that purpose\, an elastic wing was designed and manufactured using rapid prototyping. The wing was t ested at the Technion’s subsonic wind-tunnel at subcritical points and a ll the way to flutter.\nThe current study presents the flutter predictio n methodology and process as conducted numerically and in two wind tunnel experiments. The structural responses used for ARMA system identification are acceleration and strains (measured by strain gauges) in the first wi nd-tunnel test\, and strains measured via optical fibers in the second te st. The study presents comparison of the flutter prediction capability wh en based on discrete\, spars measurement (accelerometers\, strain gauges) versus that from more dense measurement (optical fibers). The study focus es on the practical aspects of the application of the method in wind-tunne l testing\, which is also of great importance for flight testing. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-365@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181017T163000 DTEND;TZID=Asia/Jerusalem:20181017T173000 DTSTAMP:20230527T135752Z URL:https://aerospace.technion.ac.il/events/investigation-of-mobile-robot- time-optimal-trajectories-under-state-dependent-constraints/ SUMMARY:Investigation of Mobile Robot Time Optimal Trajectories under State Dependent Constraints DESCRIPTION:Lecturer:Polina Khmelniker\n Faculty:Department of Aerospace En gineering\n Institute:Technion – Israel Institute of Technology\n Locati on:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abst ract: \n Details: \n As the use of autonomous robotic vehicles is increasi ng in everyday applications\, issues regarding the performance of these ve hicles become important research problems. The main performance concerns a re optimization issues\, such as travel time\, length and energy expenditu re.\n\nThis thesis studied the time optimal navigation problem of an auton omous mobile robot\, navigating in a planar environment containing a singl e polygonal obstacle. The robot is subjected to state-dependent safety con straints that prevent an inevitable collision with the obstacle during nav igation. The mobile robot is also subject to a constraint on its minimal t urning radius.  While being subjected to these constraints\, the goal of the mobile robot is to navigate from a given start point and heading to a target point\, which can possibly be located on the obstacle boundary (a d ocking problem).   The thesis obtained analytical and numerical results concerning the safe time optimal path. Specifically\, the safe time optima l path consists of three types of path primitives: minimum radius of turn circular arcs\, full linear acceleration\, and generalized cycloid curves which represent navigation at speeds on the verge of inevitable collision with the obstacle. Extensive numerical examples will demonstrate the resul ts. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-361@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181022T163000 DTEND;TZID=Asia/Jerusalem:20181022T173000 DTSTAMP:20230527T135635Z URL:https://aerospace.technion.ac.il/events/leading-edge-vortex-as-a-high- lift-mechanism-for-large-aspect-ratio-wings/ SUMMARY:Leading-Edge Vortex as a High Lift Mechanism for Large Aspect Ratio Wings DESCRIPTION:Lecturer:Hadar Ben-Gida\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n A stationary Leading-Edge-Vortex (LEV) formed over the u pper wing surface is one of the primary mechanisms to achieve high lift fo rce on wings. While most applications of LEVs have utilized the phenomenon to enhance the lift of slender wings\, evidence in nature suggests that s tationary LEVs can also exist on high aspect ratio (AR) wings.\nThis study investigates the analytical potential flow modeling of a stationary LEV a bove a high AR wing for lift enhancement. The main objective of this resea rch is to study and characterize the phenomenon for designing large AR win gs with high lift due to the LEV.\nThe novelty of the flow model we develo ped is in the three-dimensional aspects of the LEV\, which are considered in two ways:\n\n\n satisfying conservation of mass and vorticity within t he LEV core\;\n using a combination of both the strip theory and the lift ing-line theory\, in order to account for the effect of the wing shape and induced flow on the formation of a stationary LEV.\n\nOur pseudo-three-di mensional flow model is studied for several wing configurations\, in order to evaluate the resulting LEV characteristics and aerodynamics coefficien ts. Our results shed extensive insight on the physical mechanisms responsi ble for generating and maintaining a stationary LEV structure on a non-sle nder wing. The wing planform shape and sweep are shown to have a major rol e in determining the characteristics of the LEV- which can result in signi ficant lift enhancement of over 70% for a given planform. The flow model c an serve as a preliminary tool in designing new high AR wings that utilize the stationary LEV phenomenon to improve performance at high angles of at tack. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-362@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181024T163000 DTEND;TZID=Asia/Jerusalem:20181024T173000 DTSTAMP:20230527T135651Z URL:https://aerospace.technion.ac.il/events/miracles-building-and-applying -a-high-fidelity-cfd-tool-for-aerospace-engineering-problems/ SUMMARY:MIRACLES: Building and Applying a High-Fidelity CFD Tool for Aerosp ace Engineering Problems DESCRIPTION:Lecturer:Dr. Yann Delorme\n Faculty:Faculty of Mechanical Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Over the past twenty years\, the field of Computational Fluid Dynamics (CFD) has been evolving drastically\, following the progres s of computational resources and hardware. The past few years\, Large Eddy Simulation (LES) has become more and more popular\, solving for instantan eous large scales of the turbulent flow field while modeling the smallest scales\, assumed to be universal. My research focus on the development and implementation of high order accurate numerical methods to solve filtered Navier-Stokes equations in the context of Large Eddy Simulation. It is ge nerally accepted in the community that high order low dissipative numerica l methods are needed to accurately capture and predict the large scales of turbulent flows. This presents a challenge when trying to simulate realis tic complex geometries as high order numerical methods typically benefit f rom the use of structured Cartesian meshes.\nIn this seminar\, I will pres ent the latest developments of an in-house solver developed at the CFDLab at the Technion (MIRACLES). This solver combines the use of high order ene rgy stable numerical methods with an Immersed Boundary Method to allow acc urate simulations of complex practical problems. I will go over some detai ls of the methods and present several examples related to the aerospace in dustry. I will then present how this solver was recently coupled to severa l modules to allow for noise prediction of impellers\, and for the computa tion of high speed reacting flows in the context of designs of scramjets. Future developments of the solver are finally discussed. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-368@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181031T163000 DTEND;TZID=Asia/Jerusalem:20181031T173000 DTSTAMP:20230527T135838Z URL:https://aerospace.technion.ac.il/events/lunar-habitats-more-than-engin eering-issues-and-concepts/ SUMMARY:Lunar Habitats: More Than Engineering – Issues and Concepts DESCRIPTION:Lecturer:Prof. Haym Benaroya\n Faculty:Department of Mechanical and Aerospace Engineering\n Institute:Rutgers University\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n A summary of the lunar environment is provided as background to the issues that await resolution by structural engineers who will desig n habitats for long-term stays on the Moon\, initially by pioneering astro nauts\, and eventually by people who will call the Moon their home.\nKey e nvironmental concerns are the radiation and micrometeoroid environment\, t he hard vacuum\, and the lack of atmosphere. The lunar dust poses a carcin ogenic hazard\, as well as an existential threat to engineered systems. St ructures need to be designed with an eye to the psychological wellbeing of the inhabitants.\nThis presentation provides an introduction into:\n• t he recent history of lunar habitat concepts\,\n• the space and lunar env ironment\,\n• physiological and psychological challenges\,\n• the econ omics of lunar habitats\n• some lunar habitat designs\, and\n• a sampl e design concept.\n\nA 16 m diameter inflatable habitat is depicted and co uld accommodate the needs of a dozen astronauts living and working on the surface of the Moon. Depicted are astronauts exercising\, a base operation s center\, a pressurized lunar rover\, a small clean room\, a fully equipp ed life sciences lab\, a lunar lander\, selenological work\, hydroponic ga rdens\, a wardroom\, private crew quarters\, dust-removing devices for lun ar surface work\, and an airlock. The top level shows joggers required to run with their bodies almost parallel to the floor as a result of the low gravity. This artist’s concept reflects the evaluation and study at John son Space Center by the Man Systems Division and Johnson Engineering perso nnel. S89-20084\, July 1989. (Courtesy G. Kitmacher\, NASA) CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-359@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181105T163000 DTEND;TZID=Asia/Jerusalem:20181105T173000 DTSTAMP:20230527T135559Z URL:https://aerospace.technion.ac.il/events/green-aircraft-technologies-me thodologies-and-results/ SUMMARY:Green Aircraft Technologies Methodologies and Results DESCRIPTION:Lecturer:Prof. Ruxandra Mihaela Botez\n Faculty:École de Techn ologie Supérieure\n Institute:University of Quebec\, Montréal\, Canada\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Two main research projects that are developed at the Applied Research Laboratory in Active Controls\, Avionics and AeroS ervoElasticity LARCASE are presented in the area of green aircraft technol ogies. In the first research project\, three sub-projects will be presente d in the area of green aircraft modeling and simulation based on flight te sts: 1) the development of a high-fidelity simulation model of the Cessna Citation X that is efficient\, flexible and responsive for the needs of th e research in aerospace\, 2) aircraft parameter estimation from flight tes ts\, and 3) the aircraft trajectory prediction using the aero-propulsive m odel derived from flight tests. This research was realized thanks to the R esearch Aircraft Flight Simulator (RAFS) that is equipped with the flight dynamics certified at the highest Level D for one of the fastest business jet aircraft Cessna Citation X. The aim of this first research project is to demonstrate a valid methodology that could be used in the Aerospace Ind ustry with the aim to reduce the number of flight tests (thus\, their cost s) needed to validate the aircraft models.\nIn the second multidisciplinar y project\, two sub-projects will be presented in the area of morphing win g for green aircraft technologies development. In both projects\, a differ ent morphing wing was designed and manufactured with the aim to reduce dra g and to delay the flow transition\, therefore the fuel consumption\; the morphing wing was equipped in both sub-projects with piezoelectric pressur e sensors. The morphing wing shapes were changed using different types of actuation systems\, as detailed for each sub-project: 1) classical wing-bo x equipped with smart material actuators\, and 2) regional jet wing equipp ed with in-house electrical actuators. The multidisciplinary (aerodynamics \, structural and controls) research methodologies and results will be pre sented. All these projects are realized in collaboration with Canadian aer ospace companies. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-29@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181106T080000 DTEND;TZID=Asia/Jerusalem:20181106T173000 DTSTAMP:20221030T083442Z URL:https://aerospace.technion.ac.il/events/workshop-on-adjoint-based-turb omachinery-optimization-and-uncertainty-quantification-in-gas-turbines/ SUMMARY:Workshop on Adjoint Based Turbomachinery Optimization and Uncertain ty Quantification in Gas Turbines DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Facu lty Library (Room 165)\n Zoom: \n Abstract: \n Details: We will be once ag ain hosting a turbomachinery workshop\, this time titled "Workshop on Ad joint Based Turbomachinery Optimization and Uncertainty Quantification in Gas Turbines". The two distinguished guest lecturers are Prof. Francesco M ontomoli and Prof. Tom Verstraete\, from Imperial College of London and Vo n Karman Institute for Fluid Dynamics respectively.\nThe event will take p lace on November 6th\, 2018 in the Aerospace Faculty Library (Room 165) fr om 08:00 till 17:30.\nClick here for the program.\n\nThe training activiti es will be open for all students\, industry and academic staff.\nThere is no cost for registration\; however it is mandatory for all participants.\n Please reserve your spot until 21/10/2018 by contacting Vered Seginer < \;veredseg@technion.ac.il>\;\, with subject line  "Turbomachinery Work shop Registration 2018"\, indicating the full name and affiliation of all participants.\n CATEGORIES:Events LOCATION:Aerospace Faculty Library (Room 165) END:VEVENT BEGIN:VEVENT UID:0-357@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181107T163000 DTEND;TZID=Asia/Jerusalem:20181107T173000 DTSTAMP:20230527T135515Z URL:https://aerospace.technion.ac.il/events/regional-positioning-using-a-l ow-earth-orbit-satellite-constellation/ SUMMARY:Regional Positioning Using a Low Earth Orbit Satellite Constellatio n DESCRIPTION:Lecturer:Tomer Shtark\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Satellite navigation constellations orbit the Earth in med ium and geosynchronous orbits. These high altitudes raise the operational and launching costs\, but provide wide coverage\, which may be redundant i f only regional coverage is needed. Low Earth orbit satellites\, on the ot her hand\, suffer from reduced coverage capabilities\, among other issues. \nThis research develops methods for designing low Earth orbit satellite c onstellations\, aimed at position determination at a predefined geodetic r egion. This problem is solved by two strategies: spreading the satellites in a time-varying latitude strip\, or spreading them over few orbital plan es. The former strategy produces a relatively high revisit frequency\, but requires a relatively high number of orbital planes\, and produces a rela tively low coverage duration. The latter strategy produces long coverage d urations\, requires significantly fewer orbital planes\, but produces a lo wer revisit frequency. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-348@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181121T163000 DTEND;TZID=Asia/Jerusalem:20181121T173000 DTSTAMP:20230527T135108Z URL:https://aerospace.technion.ac.il/events/soft-biological-tissues-penetr ation-mechanics/ SUMMARY:Soft Biological Tissues Penetration Mechanics DESCRIPTION:Lecturer:Maor Shoshan\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Recent progress in experimental biomechanics has provided reliable hyperelastic constitutive parameters for a variety of soft biolog ical tissues like brain\, kidney and liver. These laboratory verified stra in energy functions enable accurate analytical and numerical evaluation of complicated mechanical response of soft bio tissues\, at large strains. A dvances in diagnosis\, numerical simulation and design of medical procedur es have followed accordingly. In particular\, research of soft tissues bal listic impact phenomena (perforation and penetration) is now within the fr amework of nonlinear continuum mechanics. This development stands in marke d contrast to earlier studies\, performed over decades\, where substitute materials like ballistic soap or ballistic gelatin were used to assess the resistance of bio tissues to ballistic impact.\nThe present work aims at deriving a basic theory of the mechanics of deep penetration of rigid proj ectiles into soft tissues. The study centers on the cavitation model which has been successfully employed in solid targets penetration analysis. The underlying assumptions are rigid point headed projectiles\, normal impact at small firearms velocity range and straight penetration path. Material behaviour is hyperelastic\, isotropic and incompressible\, with simple fai lure criteria. Inertia effects are accounted for and both spherical and cy lindrical patterns are considered.\nWe start with a brief historical revie w of soft tissues penetration mechanics (hyperelastic material behavior an d cavity expansion method)\, discussing several open questions which have motivated the present work. New elegant solutions for steady state cavitat ion fields will be presented next\, including derivation of several formul ae for the cavitation pressure.\nWe shall examine sensitivities of the cav itation pressure to material parameters (type of tissue)\, failure criteri a and presence of material inertia. Also discussed is the difference betwe en spherical and cylindrical cavitation patterns. Finally\, assuming that tissue resisting force applied on the projectile is given essentially by t he cavitation pressure\, we shall estimate the penetration depth and compa re with available experimental data.\nAs not much work of similar nature h as been done\, possible limitations of the present results will be discuss ed along with suggestions for future research. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-355@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181128T163000 DTEND;TZID=Asia/Jerusalem:20181128T173000 DTSTAMP:20230527T135440Z URL:https://aerospace.technion.ac.il/events/electromechanical-system-for-s olid-rocket-motor-thrust-modulation/ SUMMARY:Electromechanical System for Solid Rocket Motor Thrust Modulation DESCRIPTION:Lecturer:Yossi Zamir\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The thrust of a solid rocket motor (SRM) mainly depends on the combustion chamber pressure\, nozzle geometry and propellant character istics. The most commonly used method for a prescribed thrust profile desi gn relies only on propellant grain geometry. This method is limited and do es not comply with all the needs and requirements of rocket motors. Real t ime thrust modulation can significantly extend mission versatility and per formance of SRM based missiles. One group of methods for real time thrust modulation is based on modification of the nozzle throat area\, either dir ectly by moving parts\, or effectively by aerodynamic means. Another group of methods for thrust modulation deals with modification of the propellan t grain burn rate by different means. Reducing the throat area\, or increa sing the burn rate\, increases the pressure and thrust of the motor\, and vice versa.\nThis work includes a literature survey\, description of requi rements\, review of concepts\, design and experimentation of an electromec hanical system for real time thrust modulation of a SRM. The design is bas ed on a movable pintle against a fixed nozzle. The system is integrated wi th an existing generic rocket motor employing a propellant with a relative ly high pressure exponent (0.5). The propellant is free of metal particles in order to limit the maximum chamber temperature to 3000K and avoid exte nsive erosion and particle accumulation on critical surfaces. The system c omponents are thermally insulated in order to withstand the harsh conditio ns of the motor operation for a sufficient amount of time. The components exposed to the most challenging conditions of the nozzle area are made of materials such as molybdenum and tungsten. System operation and thrust mod ulation are demonstrated successfully. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-358@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181210T163000 DTEND;TZID=Asia/Jerusalem:20181210T173000 DTSTAMP:20230527T135539Z URL:https://aerospace.technion.ac.il/events/a-projected-lloyds-algorithm-f or-coverage-control-problems/ SUMMARY:A Projected Lloyd’s Algorithm for Coverage Control Problems DESCRIPTION:Lecturer:Yoav Palti\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n This work presents a new approach for solving the coverage p roblem for large areas given a limited number of sensors. We consider the problem where there is a given area needed to be covered\, however there are not enough sensors to provide complete coverage of the designated ar ea at once. Furthermore\, we require that at each stage of coverage\, a s ub-region in the area is constantly monitored. Lastly\, we desire a coordi nated formation\, where the distance between the agents is controlled.\nT he solution approach is a combination of two algorithms. First\, the area is being partitioned into sub-regions using a modified version of the wel l known Lloyd’s Algorithm that we term the Projected Lloyd’s Algorith m. Then\, for each sub region\, we utilize Lloyd’s Algorithm. For the c oordinate formation\, we combined Lloyd’s Algorithm with formation contr oller.\nThe new algorithm\, projected Lloyd's algorithm\, is used for cons training the area partitioning to include the required sub-region in each partition\, and it’s being achieved by projecting the algorithm result s onto the constrained polygon. Another concept that was tested is combin ing the Lloyd's algorithm strategy with distance-based formation control\, which resulted with stable controller. The strategies were tested using numerical simulations. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-345@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181217T163000 DTEND;TZID=Asia/Jerusalem:20181217T173000 DTSTAMP:20230527T135005Z URL:https://aerospace.technion.ac.il/events/transition-to-turbulence-over- convex-surfaces-and-utilization-of-instabilities-for-optimal-laminar-separ ation-delay/ SUMMARY:Transition to Turbulence Over Convex Surfaces and Utilization of In stabilities for Optimal Laminar Separation Delay DESCRIPTION:Lecturer:Dr. Michael Karp\n Faculty:Center for Turbulence Resea rch\, Faculty of Mechanical Engineering\n Institute:Stanford University\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \ n Abstract: \n Details: \n Understanding flow instability mechanisms in bo undary layers is valuable for designing more efficient aerodynamic and hyd rodynamic surfaces. This talk consists of two parts\; the first discusses instabilities and transition to turbulence in boundary layers over convex surfaces\, such as a wing’s leading edge. The second part discusses the utilization of instability mechanisms for optimal separation delay.\nContr ary to flows over concave surfaces\, which are prone to the Görtler insta bility\, boundary layers over convex surfaces are stabilized as a result o f the curvature. Nevertheless\, non-modal mechanisms may enable significan t disturbance growth which can make the flow susceptible to secondary inst abilities. The influence of curvature on primary and secondary instabiliti es is investigated theoretically and numerically. The predictions of local stability theory are verified by direct numerical simulations\, which dem onstrate that only sufficiently long and energetic streaks trigger the bre akdown to turbulence.\nFlow separation often leads to reduced aerodynamic performance. Passive control devices\, such as vortex generators\, success fully delay separation by triggering turbulence. Although the turbulence i nduces flow reattachment\, its adverse effects are increased drag and heat transfer. Moreover\, finding the optimal parameters for the design of vor tex generators is oftentimes based on trial and error\, especially their s panwise spacing. Our aim is to find the optimal perturbation that one need s to generate\, such that the separation location is delayed as downstream as possible. It is shown that a perturbation from linear stability theory leads to significant delay of separation and serves as a good starting po int for the nonlinear optimization algorithm. The mechanism responsible fo r separation delay is a mean flow distortion\, generated by nonlinear inte ractions during the non-modal growth stage. The mean flow distortion augme nts the velocity close to the wall\, counteracting the velocity decelerati on in that region. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-354@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181219T163000 DTEND;TZID=Asia/Jerusalem:20181219T173000 DTSTAMP:20230527T135421Z URL:https://aerospace.technion.ac.il/events/column-buckling-with-non-ideal -boundary-conditions/ SUMMARY:Column Buckling with Non-Ideal Boundary Conditions DESCRIPTION:Lecturer:Tomer Meir\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Buckling of a slender elastic column under static compressiv e load is a fundamental and classical problem in structural stability. It has been examined over more than 250 years\, starting with Euler and up to present day. For combinations of the ideal boundary conditions – simple \, clamped\, sliding and free -- exact analytical solutions for critical l oads are available. In real structures however\, end fixations of columns are not ideal but rather restrained by elastic end supports\, two at each end. For elastic supports\, critical loads have been determined numericall y for several cases\, yet a comprehensive stability analysis covering all possible combinations of elastic end conditions is still missing. Mathemat ically\, the buckling loads are obtained as roots of transcendental equati ons that include four constants of the end restraint springs.\nThe present research aims at a complete (once and for all) mapping of the buckling lo ads for entire possible combinations of elastic boundary conditions. Speci fically\, compact design charts\, in a user-friendly format\, are presente d along with several elegant formulae for buckling loads within definite l imits of validity. In addition\, we extend the findings for elastic buckli ng into the plastic range\, where pre-buckling stresses are higher than th e yield stress. Analysis is within the framework of Euler buckling theory of homogeneous columns with constant bending stiffness.\nWe start with an earlier reformulation of the governing transcendental equation where the f our spring constants are regrouped into just three parameters: two equival ent spring parameters and one nondimensional measure of supports asymmetry . The equation is then factorized into two distinct branches that are exam ined separately.  New closed form expressions are derived for several cas es and numerical charts are supported by accurate asymptotic expansions. C omparison with available solutions confirms the efficiency of suggested ap proach to the buckling problems.\nA detailed sensitivity analysis reveals the nonlinear effect of elastic end supports and ends asymmetry on the buc kling load. Among the cases examined in detail are rigid body instability\ , weak columns (applicable to MEMS)\, symmetric torsional springs and mult iple roots. Also discussed are the buckling energy partition and influence of supports age deterioration. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-346@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181224T163000 DTEND;TZID=Asia/Jerusalem:20181224T173000 DTSTAMP:20230527T135026Z URL:https://aerospace.technion.ac.il/events/study-of-a-ducted-rocket-with- a-hybrid-gas-generator/ SUMMARY:Study of a Ducted Rocket with a Hybrid Gas Generator DESCRIPTION:Lecturer:Daniel Komornik\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n Air-breathing engines as ramjets\, scramjets\, turbojet s\, and turbofans have higher specific impulse and energetic performance a nd\, hence\, longer range for the same amount of fuel than rockets. Ramjet s operate at high Mach numbers\, typically within the rocket flight speed range of Mach 2-5\, beyond the efficient operating flight speeds of turboj et engines. The ducted rocket (ram-rocket) is one of the types of ramjet e ngines\, which may be considered for different missiles (e.g.\, long range air to air missiles or supersonic cruise missiles). It consists of two co mbustion chambers: a gas generator chamber where fuel is burned with a sma ll amount of oxidizer (a fuel-rich propellant combination) to generate fue l-rich gases\; and a ram combustor where the gases generated in the first chamber are introduced and burned further with ambient air coming through inlets.\nThis study presents a ducted rocket (DR) using a hybrid gas gener ator. Such a novel arrangement may exhibit improved safety (due to the sep aration of fuel and oxidizer)\, availability\, better performance\, contro llability\, and a possible operation with a lower content of oxidizer in t he gas generator. The present study simulates flight at Mach 2.5 at an alt itude of 3 km. Over 150 successful static firing tests of a ducted rocket with a hybrid gas generator have been performed. These tests took place in a connected pipe facility\, simulating multiple ramjet inlet and gas gene rator conditions. Characteristic velocity efficiency was between 0.8 and 1 . Fuel regression rate at the gas generator is displayed. Based on the tes t performed\, it is demonstrated that thrust and fuel-to-air ratio can be controlled via modulating the cold oxidizer flow rate over a broad range o f missions and flight conditions. This cold flow control is one of the maj or advantages of using a hybrid gas generator for a ducted rocket. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-350@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181226T163000 DTEND;TZID=Asia/Jerusalem:20181226T173000 DTSTAMP:20230527T135148Z URL:https://aerospace.technion.ac.il/events/development-of-adaptive-cycle- micro-turbofan-engine-for-uas-applications/ SUMMARY:Development of Adaptive Cycle Micro-Turbofan Engine for UAS Applica tions DESCRIPTION:Lecturer:Michael Palman\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n The current research is focused around the development o f a variable cycle micro-turbofan engine an existing micro-turbojet with l ess than 1kN thrust. The project involves the conversion of a single spool micro turbojet via integration of a fan\, a continuously variable transmi ssion (CVT) and a variable bypass nozzle.\nAs the micro gas turbine market suffers from restrained design costs\, in order to shorten the design pro cess to a minimum\, the aspiration is to entail as few changes as possible to the core design. The solution\, analyzed in the scope of this work\, s ignificantly improves maximum thrust\, reduces fuel consumption by maintai ning the core independently running at its optimum\, and enables a wider o perational range\, all the meanwhile preserving a simple single-spool conf iguration. Moreover\, the introduction of a variable fan coupling would al low real-time optimization for several operational modes. Small gear ratio would yield a lower fan bypass ratio\, and therefore performance resembli ng a turbojet suitable for high speed flight\, whereas large gear ratio wo uld alter the engine cycle towards a modern turbofan\, which provides impr oved fuel consumption during loitering and take-off. Thus\, a small UAV eq uipped with this high-performance and cost-effective variable-gear-speed t urbofan\, would be able to operate efficiently in both "fly-fast" and "loi ter" modes.\nIn addition\, the acquired thrust increase translates into gr eater take-off weight\, while independently varying bypass area and fan sp eed enables transonic flight and general reduction in fuel consumption. Th e combination of these effects yields an increase in range and loiter time . The aircraft architecture equipped with this adaptive engine can enable realization of unique missions that were prior unattainable or required di fferent UAV propulsion systems. These unique characteristics are explored in a set of realistic scenarios. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-347@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20181231T163000 DTEND;TZID=Asia/Jerusalem:20181231T173000 DTSTAMP:20230527T135047Z URL:https://aerospace.technion.ac.il/events/nonlinear-aerodynamic-effects- on-static-aeroelasticity-of-flexible-missiles/ SUMMARY:Nonlinear Aerodynamic Effects on Static Aeroelasticity of Flexible Missiles DESCRIPTION:Lecturer:Dmitry Tihomirov\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n The general trend in missile development is towards lo nger\, faster\, high-maneuverability missiles. This makes missiles increas ingly more flexible and therefore more susceptible to aeroelastic effects\ , such as static and dynamic aeroelastic instability\, and stability probl ems due to thrust misalignment. While most past problems of missile aeroel asticity were of control surfaces flutter\, modern missile configurations experience static aeroelastic phenomena\, which are not addressed much in the literature. The current study focuses on nonlinear aerodynamic effects on the flight of elastic missiles and examines these effects for a range of angle of attack and Mach number values. The investigation is based on s tatic aeroelastic analyses of flexible missile configurations that are per formed using linear and nonlinear aerodynamic models.  The nonlinear aero elastic solution is based on the solution of the Navier-Stokes equations o n the elastically deformed missile in a Computational Fluid Dynamics (CFD) code. It serves to study the load distribution over the missile\, the res ulting deformed shape of the missile\, and the integral aerodynamic coeffi cients compared to those computed with linear aerodynamics.\nThe study pro poses a computationally efficient approach for the aeroelastic analysis of flexible missiles via a Nonlinear Strip Model (NSM). In the NSM\, the non linear aerodynamic force coefficients in each strip (segment) over the mis sile's body are computed for the rigid configuration. A database of coeffi cients\, computed for various Mach numbers and angle of attack values\, is used together with the structural modal model to provide the aeroelastic solution.\nThe test case of this study is that of a generic\, flexible mis sile configuration in various flight conditions. The elastic deformation o f the missile's body significantly reduces the stability of the configurat ion\, which\, at some conditions\, becomes unstable. Nonlinear aerodynamic effects further reduce the missile's stability and are critical for accur ate prediction of the stability margin. The NSM accurately predicts the no nlinear aeroelastic solution without relying on a computational expensive aeroelastic simulation in a CFD code. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-351@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190102T163000 DTEND;TZID=Asia/Jerusalem:20190102T173000 DTSTAMP:20230527T135209Z URL:https://aerospace.technion.ac.il/events/finding-the-shortest-3d-paths- with-curvature-constraint-in-close-range-scenarios/ SUMMARY:Finding the Shortest 3D paths with Curvature Constraint in Close Ra nge Scenarios DESCRIPTION:Lecturer:Rafi Kfir\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The problem of finding optimal trajectories is a basic proble m in aerospace engineering with many different solution algorithms. One wi dely investigated branch is the problem of finding shortest paths under ma ximum curvature constraint. The shortest planar trajectories under curvatu re constraint are the well-known Dubins paths\, which can either be arc-li ne-arc or arc-arc-arc combinations. In recent years few works dealt with 3 D shortest paths under the curvature constraint. Theoretical works prove t he existence of 3 types of spatial shortest trajectories: 3D arc-line-arc\ , 3D arc-arc-arc and helicoidal-arc. Some further works proposed algorithm s for finding the first one (3D arc-line-arc trajectories)\, which is the shortest path when the start and the end point are far from each other.\nT his work first proposes an algorithm to calculate 3D arc-arc-arc type traj ectories\, (the solution for 3D arc-line-arc is already known)\, followed by an investigation of the helicoidal-arc type trajectory. In the case of helicoidal-arc the exact solution depends on a high order TPBVP (Two Point Boundary Value Problem)\, a difficult numerical problem. In this study we propose to approximate the helicoidal-arc with polynomials. The approxima te polynomial solutions are compared to the optimal paths obtained from nu merical integration and validated by GPOPS (General Purpose OPtimal Cont rol Software). It is shown that the solutions based on the polynomials le ad to good approximation of the optimal trajectories. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-356@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190109T163000 DTEND;TZID=Asia/Jerusalem:20190109T173000 DTSTAMP:20230527T135457Z URL:https://aerospace.technion.ac.il/events/aft-sting-mount-effects-on-mis sile-longitudinal-stability-and-base-flow-characteristics/ SUMMARY:Aft-Sting Mount Effects on Missile Longitudinal Stability and Base Flow Characteristics DESCRIPTION:Lecturer:Amir Mittelman\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Aft-sting mount is the most common method of mounting wi nd tunnel models when performing aerodynamic (balance) measurements in win d tunnels\, especially when testing missile configurations. The influence of this type of mount on the base pressure and drag characteristic has bee n widely investigated in the past\, both by wind tunnel testing and Comput ational Fluid Dynamics (CFD). However\, its influence on the longitudinal stability of the tested configuration has been poorly addressed.\nAnother aspect of great interest regarding the aft-sting mount is its effect on th e flow characteristics in the near wake of the body. Several studies have shown that the presence of an aft-sting mount could significantly modify t he shear layer characteristics (e.g.\, the reattachment point\, velocity f luctuation frequencies etc.).\nThis work presents a comprehensive investig ation of these two topics. Subsonic and transonic wind tunnel tests have b een conducted with various sting to body diameter ratios\, clearly showing the aft-sting’s effect on the tail aero-surfaces contribution to the lo ngitudinal stability. Furthermore\, hot-wire anemometer has been used in s ubsonic flow conditions for mapping the near wake flow field modifications in the presence of the aft-sting. These measurements demonstrate the damp ing effect of the aft-sting mount on the shear layer velocity fluctuations . CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-349@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190114T163000 DTEND;TZID=Asia/Jerusalem:20190114T173000 DTSTAMP:20230527T135130Z URL:https://aerospace.technion.ac.il/events/aeroservoelastic-stability-ana lysis-using-response-based-parametric-flutter-margins/ SUMMARY:Aeroservoelastic Stability Analysis Using Response-Based Parametric Flutter Margins DESCRIPTION:Lecturer:Federico Roizner\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n At linear flutter onset conditions\, an aircraft under goes self-excited harmonic oscillations in response to any initial trigger \, leading to a homogenous frequency-domain flutter equation. Accordingly\ , common-flutter methods search for the conditions at which the ASE-matrix determinant is zero. The main difficulty stems from the fact that the aer odynamic force coefficients and control laws depend on the vibration frequ ency. While being well established and widely used\, the applicability of these methods is limited. Being based on the system matrix properties rath er than on response simulations\, they are not based on standard response solvers and their results are difficult to be compared with test results. The solution reflects an actual physical situation only at the flutter poi nt because it consists of adding an artificial term that is canceled only at this point. Hence\, it is difficult to obtain flutter margins with resp ect to practical design parameters. Due to their non-direct nature\, the c ommon solvers cannot be extended directly to the investigation of nonlinea r effects.\nIn this seminar\, the recently developed Parametric Flutter Ma rgin (PFM) method that uses a different flutter search strategy will be pr esented. It is based on calculating flutter margins with respect to a stab ilizing parameter\, which is added to the nominal system\, via frequency r esponse functions of the stabilized system. The combination of the PFM met hod with the Increased-Order Modeling approach facilitates the application of PFM to nonlinear flutter that yields LCO. It will be also shown that t he PFM method can be applied for performing efficient sensitivity analysis . A considerable advantage of the PFM method is that the frequency-respons e functions at and beyond the flutter boundary of the nominal system are c alculated with a stable system. This allows us to perform safe-flutter tes t in which the aeroelastic model is stabilized\, and the flutter-onset con ditions of the nominal system are positively identified. Two PFM-wind-tunn el flutter tests were performed\, a proof-of-concept one in TU-Delft using a 2D-aeroelastic wing\, and one in the Technion subsonic wind tunnel usin g a more realistic-3D aeroelastic model. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-353@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190121T163000 DTEND;TZID=Asia/Jerusalem:20190121T173000 DTSTAMP:20230527T135401Z URL:https://aerospace.technion.ac.il/events/unsteady-supersonic-flow-over- a-spiked-blunt-body/ SUMMARY:Unsteady Supersonic Flow over a Spiked Blunt Body DESCRIPTION:Lecturer:Devabrata Sahoo\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n Blunt nose shapes such as flat-face\, hemisphere and el lipse are of supreme interest among the bodies moving at supersonic speeds due to the need for housing payloads\, radar or infrared seekers. This bl untness in the nose shape leads to high drag. One common solution for drag reduction is the use of a spike\, a slender rod mounted at the stagnation point. Unfortunately\, past studies have reported various types of unstea diness associated with mounted spikes. These oscillations could be detrime ntal to the purpose of the spike\, flow stability and the vehicle structur e itself. The main motivation for the present study is to gain a better un derstanding of the mechanism involved behind this flow unsteadiness in ord er to control and alleviate it.\nIn the present research\, three different forebody shapes (flat-face\, hemispherical and elliptical) mounted with a sharp tip spike are considered. First\, parametric studies have been carr ied out to investigate the sensitiveness of the spike and forebody geometr y on the drag reduction as well as flow unsteadiness. Then\, the flow unst eadiness arising over these configurations are captured and differentiated . The mechanism behind the shock related unsteadiness has been proposed qu alitatively using time-resolved high-speed shadowgraphs and explained quan titatively using unsteady pressure measurements along with the data based modal decomposition methods and numerical simulations. Proper Orthogonal D ecomposition (POD) and Dynamic Mode Decomposition (DMD) methods have been used to extract and study the dominant spatio-temporal modes. Finally\, on e example of unsteadiness alleviation has been demonstrated. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-352@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190123T163000 DTEND;TZID=Asia/Jerusalem:20190123T173000 DTSTAMP:20230527T135226Z URL:https://aerospace.technion.ac.il/events/2d-particle-in-cell-simulation -of-the-narrow-channel-hall-thruster/ SUMMARY:2D Particle-In-Cell Simulation of the Narrow Channel Hall Thruster DESCRIPTION:Lecturer:Omri Hamo\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In the past decade growing numbers of nanosatellites are bein g used in space\, with an-ever increasing mission demands. Nevertheless\, due to severe limitations on on-board power\, there is currently a gap in propulsion solutions for these miniaturized spacecraft. To address these i ssues\, a very low power Hall effect thruster known as the narrow channel Hall thruster (NCHT) was recently developed and demonstrated at the Aerosp ace Plasma Laboratory (APL)\, Technion. Due to the small dimensions of the NCHT channel (1 mm wide and 2 mm in length) experimental measurements of the thruster discharge are very challenging.\nIn this work we study the th ruster using a particle-in-cell (PIC) simulation XOOPIC-APL. The original code was modified to provide 2D spatial distributions of the plasma parame ters inside the thruster channel. The global performance figures obtained from the simulation are shown to be in excellent agreement with the experi mental measurements.\nThe talk will be divided into two parts: first we pr esent the numerical techniques that were used to improve the code executio n\; second\, we analyze the simulation results. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-329@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190130T163000 DTEND;TZID=Asia/Jerusalem:20190130T173000 DTSTAMP:20230527T132438Z URL:https://aerospace.technion.ac.il/events/combustion-of-boron-based-pyro technic-compounds/ SUMMARY:Combustion of Boron Based Pyrotechnic Compounds DESCRIPTION:Lecturer:Yair Solomon\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Boron based gelled fuels are promising candidates for cert ain future ramjet applications\, offering potential improvements in perfor mance and/or safety over conventional liquid and solid systems. For this p urpose\, a fundamental understanding of combustion of gel droplets is requ ired and several problems of ignition and agglomeration of boron particles have to be solved.\nThis study addresses the combustion behavior of micro -pyrotechnic clusters of boron suspended in kerosene based gel fuels. The pyrotechnic clusters should ignite in the temperature range between the en d of the kerosene evaporation and the liquefaction of boron oxide. This te mperature range defines a “dry window” where the boron particles are n ot submerged in any liquid and their dispersion is not limited by the liqu id viscosity and surface tension. Operation within this time frame allows the pyrotechnic reaction to heat up and disperse the boron particles.\nThe research combines both experimental and theoretical investigations on gel combustion. In the experimental part\, pyrotechnic clusters with differen t oxidizers were tested in order to identify and understand the various ig nition and combustion phenomena of gel fuels. In addition to the combustio n tests of gel droplets\, calorimetric tests of the pyrotechnic mixture we re conducted. The theoretical part aims to determine the temperature and p ressure profiles inside the burning gel droplet. This allows determining t he existence of temperature gradients inside the droplet that produce a “dry window” during the droplet combustion. The existence of a pressur e gradient over the droplet outer layer may explain various phenomena\, su ch as secondary atomization\, that can break up the droplet into smaller p arts and improve combustion efficiency. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-335@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190206T163000 DTEND;TZID=Asia/Jerusalem:20190206T173000 DTSTAMP:20230527T134720Z URL:https://aerospace.technion.ac.il/events/dynamic-response-of-air-vehicl es-with-very-flexible-structures-to-gust-and-maneuver-commands-with-large- nonlinearities/ SUMMARY:Dynamic Response of Air Vehicles with Very Flexible Structures to G ust and Maneuver Commands with Large Nonlinearities DESCRIPTION:Lecturer:Favel Gov\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The tools necessary for the aeroelastic design of very flexib le aircraft with geometric nonlinearities are limited. The present work de scribes a novel model that integrates a modal formulation with a three-dim ensional geometrically nonlinear structural dynamic model\, for the effect ive study of very flexible aircraft structures under impulsive loads\, suc h as gusts\, that cause large displacements.\nThe presented modal formulat ion links linear segments with nonlinear coupling terms. The model nonline arity is captured by dividing the wing structure into several spanwise seg ments\, each having large rigid-body displacements but may assume to have linear elastic deformations. The required number of modes may be reduced b y using fictitious masses at the segment interfaces. The structural dynami c model based on co-rotational linear frameworks is developed\, matching t he modal formulation characteristics. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-45@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190306T090000 DTEND;TZID=Asia/Jerusalem:20190306T100000 DTSTAMP:20221030T083443Z URL:https://aerospace.technion.ac.il/events/the-59th-israel-annual-confere nce-on-aerospace-sciences-iacas/ SUMMARY:The 59th Israel Annual Conference on Aerospace Sciences (IACAS) DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Dan Panorama H otel Tel Aviv & Technion\, Haifa\n Zoom: \n Abstract: \n Details: The 59th IACAS will take place on:\nMarch 6\, 2019 – Dan Panorama Hotel\, Tel Av iv\, Israel\nMarch 7\, 2019 – Technion Campus\, Haifa\, Israel\nThe Isra el Annual Conference on Aerospace Sciences\, spanning several generations\ , is an important annual event on the calendar of the aerospace communit y in Israel and arouses a great deal of interest abroad. Taking part in th is yearly event are engineers\, scientists and experts in the field of a eronautics and astronautics\, representing well-known local aerospace agen cies and industries\, as well as participants from major research center s worldwide.\nThe two day conference covers new research\, presents up-to- date technology and provides a forum for exchanging new ideas.\n CATEGORIES:Events LOCATION:Dan Panorama Hotel Tel Aviv & Technion\, Haifa END:VEVENT BEGIN:VEVENT UID:0-67@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190306T090000 DTEND;TZID=Asia/Jerusalem:20190307T090000 DTSTAMP:20221031T095839Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%9b%d7%a0%d7%a1-%d 7%94%d7%99%d7%a9%d7%a8%d7%90%d7%9c%d7%99-%d7%94%d7%a9%d7%a0%d7%aa%d7%99-%d 7%94-59-%d7%9c%d7%9e%d7%93%d7%a2%d7%99-%d7%94%d7%aa%d7%a2%d7%95%d7%a4%d7%9 4-%d7%95%d7%94%d7%97/ SUMMARY:הכנס הישראלי השנתי ה-59 למדעי התעופה ו החלל (IACAS) DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:מלון דן פנ ורמה תל אביב + קמפוס הטכניון\, חיפה\n Zoom: \n A bstract: \n Details: \n הכנס הישראלי השנתי ה-59 למדע י התעופה והחלל (IACAS) יתקיים ביום רביעי\, 6.3. 19\, במלון דן פנורמה תל אביב\, וביום חמישי\, 7.3.19\, בקמפוס הטכניון בחיפה.\n\nכנס זה הינו\, זה למעלה מחמישים שנה\, האירוע המרכזי בחי י הקהילה האווירונאוטית במדינת ישראל. משת תפים בו כ-600 מהנדסים\, מדענים ומומחים בתחו מי האוירונוטיקה והאסטרונאוטיקה מהארץ וה עולם.\n\nבזכות ערכו המדעי והטכנולוגי הרב\, הכנס הוא מפגש חי ותוסס ומעניין גם מבחינה חברתית ועסקית. בארגונו שותפים הגופים העי קריים העוסקים באוירונוטיקה וחלל במדינה: משרד הביטחון וצה"ל\, התעשיות הביטחוניות – התעשייה האווירית לישראל\, רפאל\, תעש מע רכות\, אלביט מערכות\, סוכנות החלל הישראלי ת וכמובן האקדמיה – הטכניון\, אוניברסיטת תל-אביב ואוניברסיטת בן-גוריון. לפיכך\, מש תתפים בו דרך קבע נציגים של חברות אוירונו טיות גדולות וקטנות העוסקות בפיתוח וייצו ר בתחום.\n\nתכנית הכנס תכלול הרצאות שמחברי הן מגיעים ממדינות שונות ברחבי העולם\, בינ יהן הרצאות מוזמנות\, מהארץ ומחו"ל\, ותחרות ייחודית של פרויקטי סטודנטים. CATEGORIES:אירועים LOCATION:מלון דן פנורמה תל אביב + קמפוס הטכניו ן\, חיפה END:VEVENT BEGIN:VEVENT UID:0-334@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190313T163000 DTEND;TZID=Asia/Jerusalem:20190313T173000 DTSTAMP:20230527T132616Z URL:https://aerospace.technion.ac.il/events/space-navigation-with-an-omni- directional-vision-sensor/ SUMMARY:Space Navigation with an Omni-Directional Vision Sensor DESCRIPTION:Lecturer:Omri Kaufman\n Faculty:TASP - Autonomous Systems and R obotics\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n With the onset of autonomous spacecraft formation flyin g missions\, the ability of satellites to autonomously navigate relatively to other space objects has become essential. To implement relative naviga tion\, relative measurements should be taken\, and fused using relative st ate estimation. An efficient way to generate such information is by using vision-based measurements. Cameras are passive\, low-energy\, and informat ion-rich sensors that do not actively interact with other space object. Ho wever\, pointing cameras with a conventional field-of-view to other space objects requires much a-priori initialization data\; in particular\, dedic ated attitude maneuvers are needed\, which may interfere with the satellit e’s main mission. One way to overcome these difficulties is to use an om nidirectional vision sensor\, which has a 360-degree horizontal field of v iew.\nIn this presentation\, we will discuss the development of an omnidir ectional vision sensor for satellites\, which can be used for relative nav igation\, formation flying\, and space situational awareness. The study in cludes the development of the measurement equations\, dynamical models\, a nd state estimation algorithms\, as well as an experimental investigation conducted at the Distributed Space Systems Lab. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-333@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190318T163000 DTEND;TZID=Asia/Jerusalem:20190318T173000 DTSTAMP:20230527T132557Z URL:https://aerospace.technion.ac.il/events/buckling-of-arteries-and-other -instabilities-in-soft-tissues/ SUMMARY:Buckling of Arteries and Other Instabilities in Soft Tissues DESCRIPTION:Lecturer:Nir Emuna\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In 1809\, almost a century before the first human flight\, th e polymath Thomas Young opened his lecture “On the functions of the hear t and arteries” with the following statement:\n“The mechanical motions \, which take place in an animal body\, are regulated by the same general laws as the motions of inanimate bodies… As far\, therefore\, as the fun ctions of animal life depend on the locomotions of the solids or fluids\, those functions must be capable of being illustrated by the consideration of the mechanical laws of moving bodies: and it is obvious\, that the inqu iry\, in what manner\, and in what degree\, the circulation of the blood d epends on the muscular and elastic powers of the heart and of the arteries \, supposing the nature of those powers to be known\, must become simply a question belonging to the most refined departments of the theory of hydra ulics.”\nThis prophetic statement is materialized\, now\, more than ever . An increasing number of engineers\, mathematicians\, and physicists appl y analytical\, numerical\, and experimental methods that have matured in t hose disciplines\, to answer questions in biology. Mechanical stability an alysis\, a method well known to aeronautical\, mechanical\, and civic engi neers\, provides valuable insights into developmental processes (cortical folding\, pattern formation in gastrointestinal tissues)\, neurological di sorders (schizophrenia\, polymicrogyria\, lissencephaly)\, arterial pathol ogies (atherosclerosis\, aneurysms\, thrombosis)\, to name a few. The intr insic complexity of these tissues poses quite a few modeling challenges. M any soft tissues have a layered structure\, each layer has different\, hig hly nonlinear and anisotropic mechanical behavior.  Due to differential g rowth taking place in the layers\, residual stresses are developed. Moreov er\, the boundary and interface conditions in soft biological tissues are not known to the same level of certainty as in engineering structures.\nIn this talk\, I will be discussing the application of linear bifurcation an alysis to soft tissues within the framework of nonlinear elasticity. In pa rticular\, I will discuss twist buckling in arteries (as found in femoropo pliteal and testicular arteries)\, how sensitive are stability margins to load configuration at the onset of instability (i.e. dead-load\, follower force\, fluid-pressure)\, and how the joint effect of residual stresses an d interfacial conditions can induce spontaneous buckling (as found in esop hagus and airways). Given time\, I will also discuss the problem of sensit ivity of vascular constitutive models to uncertainties in residual stresse s data. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-46@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190327T123000 DTEND;TZID=Asia/Jerusalem:20190327T143000 DTSTAMP:20221030T083445Z URL:https://aerospace.technion.ac.il/events/the-2019-annual-faculty-gradua te-studies-research-day/ SUMMARY:The 2019 Annual Faculty Graduate Studies Research Day DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:The Aeropspace Engineering faculty's lobby\n Zoom: \n Abstract: \n Details: Graduate stu dents will present their research in poster format to a general audience\, including Faculty members\, guests from industry and other Faculties\, gr aduate and undergraduate students.\n A pre-poster session will first be h eld in Room 165\, at which graduate students will briefly present the topi c of their research using 1 or 2 slides.  This will enable visitors to fo cus on specific fields of interest and the exhibitors to promote their wor k. The posters themselves will be exhibited in the Faculty lobby\, on both 1st and 2nd floors\, by the graduate students.\n At the end of the event \, two sorts of prizes will be awarded. The best posters will be chosen af ter evaluation by a committee (comprised of Faculty members). The most pop ular poster will be chosen by the audience in a secret ballot.\n \n\n CATEGORIES:Events LOCATION:The Aeropspace Engineering faculty's lobby END:VEVENT BEGIN:VEVENT UID:0-66@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190327T123000 DTEND;TZID=Asia/Jerusalem:20190327T143000 DTSTAMP:20221031T080955Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%94%d 7%9e%d7%97%d7%a7%d7%a8-%d7%94%d7%a9%d7%a0%d7%aa%d7%99-%d7%a9%d7%9c-%d7%94% d7%9e%d7%a9%d7%aa%d7%9c%d7%9e%d7%99%d7%9d-%d7%9c%d7%aa%d7%90%d7%a8%d7%99%d 7%9d-%d7%92%d7%91%d7%95/ SUMMARY:יום המחקר השנתי של המשתלמים לתארים ג בוהים 2019 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location: אולם הכני סה לפקולטה להנדסת אוירונוטיקה וחלל\n Zoom: \ n Abstract: \n Details: \n גם השנה יתקיים בפקולטה "י ום מחקר" שבו יוצג המחקר הפקולטי לקהל רחב המורכב מחברי סגל\, אורחים מהתעשייה\, משתל מים לתארים גבוהים\, סטודנטים לתואר ראשון ואורחים מפקולטות אחרות. ביום המחקר יציגו המשתלמים לתארים גבוהים (מגיסטר ודוקטור) את מחקריהם על גבי פוסטרים.\n\nכדי לאפשר לק הל להתמקד כל אחד בנושאים המעניינים אותו יתקיים בתחילת האירוע בכתת הספרייה מושב ה צגת הפוסטרים שבו כל משתלם יציג בקצרה (עד 3 דקות) את נושא מחקרו. לאחר מכן\, יוצגו הפוס טרים ברחבת "הפטרייה"\, בקומה הראשונה והשנ ייה בפקולטה. המשתלמים המציגים יעמדו ליד הפוסטרים ויציגו למתעניינים את מחקריהם.\n\ nבתום יום המחקר יוענקו פרסים: פרסי השופטי ם (שייבחרו על ידי חבר שופטים מבין חברי הס גל) ופרס בחירת הקהל (שייבחר על ידי הצבעה ח שאית של הקהל).\n\n CATEGORIES:אירועים LOCATION: אולם הכניסה לפקולטה להנדסת אוירונו טיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-337@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190327T163000 DTEND;TZID=Asia/Jerusalem:20190327T173000 DTSTAMP:20230527T134753Z URL:https://aerospace.technion.ac.il/events/study-of-liquid-atomization-by -homogeneous-flash-boiling-mechanism/ SUMMARY:Study of Liquid Atomization by Homogeneous Flash Boiling Mechanism DESCRIPTION:Lecturer:Yahav Moshkovich\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n Over the years\, different methods have been developed in order to obtain suitable sprays for different applications. The most i mportant characteristics of a spray include the drops diameter\, droplet s ize distribution\, sprays shape\, flow velocity and mass flux. Former stud ies show that the flash boiling method is one of the most efficient method s to obtain a spray with very small droplets\, with a uniform distribution . This is relevant for many applications such as combustion systems\, for which higher combustion efficiency and low pollution are important. Today\ , flash boiling sprays are widely used to generate fine sprays in air refr eshers\, insect fighting\, painting and some pharmaceutical applications.\ nFlash boiling is obtained when a liquid at a high pressure is allowed to flow through an orifice towards a low ambient pressure\, which is below it s saturation pressure\, so bubbles nucleation is likely to occur. In fuel atomization systems\, the nucleation is followed by bubbles’ growth\, le ading to liquid jet atomization. Depending on the liquid initial temperatu re\, its critical temperature\, the ambient pressure and the rate of press ure drop\, two major types of nucleation may occur\; nucleation at the liq uid/solid interface (heterogeneous nucleation)\, and nucleation at the liq uid bulk (homogeneous nucleation).\nThe occurrence of flash boiling atomiz ation involves kinetic stability problems that are characterized by two cr iteria that include a minimal initial liquid temperature and a minimal rat e of pressure drop. In this work\, we analyze\, and suggest analytical exp ressions for those two criteria. Furthermore\, this study presents experim ental results of sprays that were generated by flash boiling mechanism in a variety of operation conditions. Those results support the findings of t he theoretical analysis. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-338@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190401T163000 DTEND;TZID=Asia/Jerusalem:20190401T173000 DTSTAMP:20230527T134810Z URL:https://aerospace.technion.ac.il/events/bounded-circumlunar-spacecraft -formations/ SUMMARY:Bounded Circumlunar Spacecraft Formations DESCRIPTION:Lecturer:Oren Fischman\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Long-term satellite formation keeping must account for th e effects of orbital perturbations. While long-term formation keeping arou nd the Earth has been thoroughly studied\, lunar formations are yet to be further explored. In comparison to the Earth\, the Moon introduces a more complex gravitational field\, and requires taking into account additional gravitational perturbations.\nIn this work\, the rates of the differential orbital elements of two lunar satellites in formation are expanded up to second order. These rates are then simplified\, assuming the chief satelli te is on a frozen lunar reference orbit. Additional assumptions are made t o simplify the variational equations further\, while retaining second-orde r terms. Numerical simulations are performed to illustrate the feasibility of using simplified rates of the differential orbital elements under vari ous perturbation mitigation techniques\, for a nominal orbit which deviate s from the assumed frozen reference orbit. These simulations are carried o ut for a variety of scenarios\, including frozen and near-frozen chief orb its\, based on an actual lunar formation flying mission. The analysis vali dates the feasibility of using perturbation mitigation techniques for futu re lunar formation flying missions. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-339@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190403T163000 DTEND;TZID=Asia/Jerusalem:20190403T173000 DTSTAMP:20230527T134827Z URL:https://aerospace.technion.ac.il/events/dipolophoresis-of-ideally-pola rizable-cylindrical-particle-pairs/ SUMMARY:Dipolophoresis of Ideally-Polarizable Cylindrical Particle Pairs DESCRIPTION:Lecturer:Shay Oren\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n We study dipolophoretic (DIP)\, i.e. the combined induced – charge electrophoretic (ICEP) and dielectrophoretic (DEP) interactions be tween a pair of identical conducting circular cylindrical particles suspen ded in an unbounded electrolyte solution and subject to a weak uniform tim e dependent external field acting in a plane perpendicular to the axes of the cylinders. Within the framework of   the thin – Debye – layer li mit\, we specifically focus on the cases of an AC field acting in a fixed direction in the plane and a constant – magnitude field rotating with fr equency\, respectively.\nBoth the ICEP and DEP result in particle mutual a ttraction when their line – of – centres (LOC) is aligned with the ext ernal field and repulsion when it is perpendicular thereto. The nonlineari ty inherent in both mechanisms gives rise to opposing effects acting to or ient the LOC parallel to the external field (DEP) or perpendicular thereto (ICEP). Thus\, at low frequencies\, when the latter prevails\, particles ultimately move apart in the direction perpendicular to the external field . With increasing frequency\, DEP prevails over ICEP in a widening domain of the plane resulting in particles eventually pairing (or chaining in mul ti-particle suspensions) along field lines. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-336@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190408T163000 DTEND;TZID=Asia/Jerusalem:20190408T173000 DTSTAMP:20230527T134735Z URL:https://aerospace.technion.ac.il/events/effect-of-distributed-surface- roughness-on-the-dynamics-of-shear-layers-including-drag-reduction-and-the -laminar-turbulent-transition/ SUMMARY:Effect of Distributed Surface Roughness on the Dynamics of Shear La yers including Drag Reduction and the Laminar-Turbulent Transition DESCRIPTION:Lecturer:Prof. J.M. Floryan\n Faculty:Department of Mechanical and Materials Engineering\n Institute:The University of Western Ontario\, Canada\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\ n Zoom: \n Abstract: \n Details: \n It has been recognized since the pione ering experiments of Reynolds in 1883 that surface roughness plays a signi ficant role in the dynamics of shear layers. This is a classical problem i n fluid dynamics but\, nevertheless\, its resolution is still lacking. Mos t of the efforts have been focused on experimental approaches that have re sulted in a number of correlations but have failed to uncover the mechanis ms responsible for the flow response. Theoretical analyses have also faile d to provide a consistent explanation of the flow dynamics. As there are a n uncountable number of possible geometrical roughness forms\, the problem formulation represents a logical contradiction as it might not be possibl e to find a general answer to a problem that has an uncountable number of variations.\nThe recent progress towards the theoretical resolution of thi s apparent contradiction will be discussed and recent results dealing with the problem of distributed surface roughness will be presented. The progr ess has hinged on the development of the immersed boundary conditions meth od and the reduced geometry concept. It will be shown that it is possible to propose a rational definition of a hydraulically smooth surface by invo king flow bifurcations associated with the presence of roughness. Successf ul resolution of roughness problems gives access to the design of surface roughness for passive flow control where drag reduction can be achieved ei ther directly\, through re-arrangement of the form of the flow that result s in the reduction of the shear stress\, or indirectly\, through delay of the laminar-turbulent transition. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-340@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190410T163000 DTEND;TZID=Asia/Jerusalem:20190410T173000 DTSTAMP:20230527T134841Z URL:https://aerospace.technion.ac.il/events/optimal-guidance-and-control-f or-imposing-impact-angle-and-time/ SUMMARY:Optimal Guidance and Control for Imposing Impact Angle and Time DESCRIPTION:Lecturer:Ronny Tsalik\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Shaping the trajectory of an interceptor is crucial for nu merous reasons\, including the ability to take into account environmental factors and countermeasures. Moreover\, we gain the ability to specify the impact angle and the intercept time.\nWe will begin the talk with an intr oduction on the inscribed-angle guidance concept\, which enables the impos ition of a required impact angle against stationary and moving targets. Th e relationship between inscribed-angle guidance and parallel-navigation wi ll be presented\, showing that a collision course can be obtained for spec ific constant inscribed-angle. Then\, a linear optimal control based guida nce law that enforces the inscribed angle guidance concept will be present ed.\nThis will be followed by the presentation of a new impact time guidan ce concept\, based on the geometric principle that constraints the interce ptor to follow a circular trajectory. Application of the guidance concept for stand-off tracking of stationary and moving targets will be demonstrat ed as well.\nFinally\, a new three-point guidance concept for simultaneous ly imposing impact angle and intercept time will be introduced. The guidan ce concept is based on a geometric principle that constraints the intercep tor to follow an elliptic trajectory. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-342@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190417T163000 DTEND;TZID=Asia/Jerusalem:20190417T173000 DTSTAMP:20230527T134915Z URL:https://aerospace.technion.ac.il/events/a-network-optimization-framewo rk-for-cooperative-control-of-passive-short-systems/ SUMMARY:A Network-Optimization Framework for Cooperative Control of Passive -Short Systems DESCRIPTION:Lecturer:Miel Sharf\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n The mathematical theory of nonlinear cooperative control re lies heavily on notions from graph theory and passivity theory. A general analysis result is known about cooperative control of maximally equilibr ium-independent passive systems\, relating steady-states of the closed-lo op system to optimal solutions of certain static convex network optimizati on problems. This relation has many applications in various areas of mult i-agent systems\, e.g. model-free control\, network identification\, and fault detection and isolation.\nHowever\, when trying to apply the framewo rk to passive-short systems directly\, it fails\, as the cost function in the optimization problem becomes non-convex\, or even undefined. We show t he network optimization framework can be extended to output-passive short systems by regularizing the said optimization problems\, inducing a passiv izing feedback term on the agents. We explore two methods of doing so. We then study systems with general shortage of passivity\, showing that a pas sivizing transformation can always be found by an analogous regularization process. We exemplify our results by case studies. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-343@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190527T163000 DTEND;TZID=Asia/Jerusalem:20190527T173000 DTSTAMP:20230527T134931Z URL:https://aerospace.technion.ac.il/events/active-control-of-fluid-struct ure-interaction-systems/ SUMMARY:Active Control of Fluid-Structure Interaction Systems DESCRIPTION:Lecturer:Assoc. Prof. Hui Tang\n Faculty:Department of Mechanic al Engineering\n Institute:The Hong Kong Polytechnic University\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n In this talk\, the use of active control to change the dynamics of idealized fluid-structure interaction (FSI) systems will be in troduced. Here the term "active control" means that the control is realize d by injecting a small amount of energy into existing FSI systems. Compare d to its counterpart\, i.e.\, passive control\, active control is adaptive and on-demand\, and hence has a much wider operating range.\nFirst\, the control of wakes and vortex-induced vibrations of a circular cylinder usin g synthetic jets (SJs) will be introduced. As an associated phenomenon\, l ock-on of vortex shedding to a pair of SJs will be discussed.\nSecond\, en hancement of flapping-foil aerodynamics using various active control metho ds\, including SJs\, leading-edge perturbations and adjustable flexibility \, will be presented.\nLast\, the adoption of machine-learning methods on active closed-loop control of a cylinder flow system will be demonstrated. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-331@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190617T163000 DTEND;TZID=Asia/Jerusalem:20190617T173000 DTSTAMP:20230527T132521Z URL:https://aerospace.technion.ac.il/events/the-2019-merhav-prize-seminar- estimation-based-guidance-using-optimal-bayesian-decision/ SUMMARY:The 2019 Seminar in Memory of Prof. Shmuel and Mrs. Noemi Merhav - Estimation-Based Guidance Using Optimal Bayesian Decision DESCRIPTION:Lecturer:Liraz Mudrik\n Faculty:Faculty of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Derived based on an idealized\, perfect information different ial game\, the acclaimed DGL1 guidance law was shown to guarantee hit-to-k ill performance in the linearized\, deterministic case\, involving an inte rceptor possessing superior maneuverability and agility. In real life scen arios\, where the perfect information assumption never holds\, this advanc ed guidance law has to be augmented with a separately designed estimator t hat provides an estimate of the missing information. However\, the inheren t estimation error leads to erroneous decisions on the part of the guidanc e law\, resulting in a severe interception performance degradation.\nTo al leviate this performance degradation\, we use Bayesian decision theory to make optimal decisions on the game’s state\, that properly take into acc ount the inherent uncertainty due to the estimation error\, on the one han d\, while also considering the cost (final miss distance) associated with making various decisions on the game’s state\, on the other hand. In tur n\, we modify the DGL1 law to use these optimal decisions\, which results in a new\, estimation-aware guidance law.\nThe implementation of the Bayes ian decision rule requires the knowledge of the game’s posterior probabi lity density function. To provide this density we employ an interacting mu ltiple model particle filter\, which is capable of dealing with nonlinear\ , non-Gaussian and even non-Markovian mode switching problems. The target acceleration command mode is modeled as a non-homogeneous Markov model\, t o cope with sophisticated targets that optimally time their evasion maneuv ers. The performance of the new guidance law is demonstrated via an extens ive Monte-Carlo simulation study\, where it is compared with the classical DGL1. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-330@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190626T163000 DTEND;TZID=Asia/Jerusalem:20190626T173000 DTSTAMP:20230527T132502Z URL:https://aerospace.technion.ac.il/events/control-and-estimation-challen ges-of-direct-exoplanet-imaging-from-space/ SUMMARY:Control and Estimation Challenges of Direct Exoplanet Imaging from Space DESCRIPTION:Lecturer:Leonid Pogorelyuk\n Faculty:Department of Mechanical a nd Aerospace Engineering\n Institute:Princeton University\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Taking an image of a planet proves to be extremely challengin g when the planet orbits a star tens of parsecs away from our sun. Light s ignals from an Earth-like exoplanets are 10 orders of magnitudes dimmer th an signals from their host stars and can only be detected by space telesco pes employing a special optical design - the coronagraph. However\, the fr action of the starlight blocked by coronagraphs suffers from manufacturing imperfections\, alignment errors\, and mechanical and thermal stresses ac ting on the instrument. These issues have to be addressed in real-time via estimation and control of the wavefront of the incoming light\, as well a s with offline image post-processing techniques.\nThe choice of observatio n and post-processing strategies has significant effect on the planet dete ctability threshold. In particular\, statistically informed reduced-order approaches may reduce the severe wavefront stability requirements on futur e space telescopes\, making them more affordable and facilitating the disc overy and characterization of habitable exoplanets. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-332@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190701T163000 DTEND;TZID=Asia/Jerusalem:20190701T173000 DTSTAMP:20230527T132538Z URL:https://aerospace.technion.ac.il/events/effect-of-poynting-robertson-a nd-solar-wind-drag-on-smart-dust-in-space/ SUMMARY:Effect of Poynting-Robertson and Solar Wind drag on Smart Dust in S pace DESCRIPTION:Lecturer:Vinayak Vadlamani\n Faculty:Department of Aerospace En gineering\n Institute:Technion – Israel Institute of Technology\n Locati on:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abst ract: \n Details: \n Due to breakthrough advances in miniaturization\, the scale of spacecraft components can now be reduced to the millimeter scale . Termed as "smart dust"\, the concept of spacecraft on a chip promises t o enable a novel category of such centimeter sized spacecraft to be flown in swarms of hundreds or even thousands. One alternative is to exploit pe rturbations like solar radiation pressure (SRP) for orbit control without using artificial forces thus yielding stable equilibrium solutions that co uld sustain mission requirements. Previous studies have investigated the effect of Poynting-Robertson and Solar Wind (PRSW) drag for interplanetary dust.\nGiven similar area-to-mass ratio to smart dust\, including Poynti ng-Robertson and Solar Wind (PRSW) drag could possibly extend the solutio n space thereby increasing the span of partial or full equilibrium solutio ns for smart dust devices. The inclusion of PRSW drag in the dynamical model was studied using averaging techniques based on Gauss Variational Equations.  The study focused on the dynamical behaviour of the relativ e perigee-sun angle and its stability as a tool for analyzing long-term ev olution. The existence of partial and full equilibria solutions was con firmed and the results are discussed in detail. Some trends with respect to different area-to-mass ratio are also presented. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-341@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190703T163000 DTEND;TZID=Asia/Jerusalem:20190703T173000 DTSTAMP:20230527T134855Z URL:https://aerospace.technion.ac.il/events/ignition-characteristics-of-pl asma-reformed-n-heptane-in-a-homogeneous-charge-compression-ignition-engin e-a-modeling-study/ SUMMARY:The 2019 Timnat Prize Seminar - Ignition Characteristics of Plasma Reformed N-Heptane in a Homogeneous Charge Compression Ignition Engine: A Modeling Study DESCRIPTION:Lecturer:Galia Faingold\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Combustion processes can be greatly improved using react ive species created in non-equilibrium plasma for the initiation of fuel o xidation and pyrolysis. One such process is volumetric ignition\, inherent to homogeneous charge compression ignition (HCCI) engines. The HCCI engin e has high efficiency and low emissions of both nitrous oxide (NO) and car bon monoxide (CO)\, and does not produce soot particles. However\, HCCI te chnology is currently limited by control difficulties and has a narrow ope rating range when compared to the traditional compression ignition or spar k ignition engines.\nThe present study seeks to control ignition timing by reforming a fuel-air mixture in a plasma discharge. A small charge of n-h eptane/air mixture is subjected to a plasma discharge and then mixed with a main charge in order to modify ignition characteristics. The effects of the reformed charge on ignition timing are investigated using zero-dimensi onal time dependent models. Plasma reaction calculations employ an open-so urce zero-dimensional discharge solver ZDPlaskin\, incorporating BOLSIG+ t o obtain electron transport coefficient and for pre-processing the plasma chemistry mechanism\, including rates of electron collision reactions. Ign ition delay of fuel-air mixture with species created in the discharge is c alculated using Cantera.\nIgnition delay was shortened significantly using a small amount of reformed fuel\, especially at low temperatures of 600 t o 800K. At higher temperatures\, the change is less pronounced\; however\, there is a decrease in ignition delay with the increase in activated spec ies molar mass. The results show potential as a method to control ignition timing in advanced engine technologies. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-326@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190708T163000 DTEND;TZID=Asia/Jerusalem:20190708T173000 DTSTAMP:20230527T132331Z URL:https://aerospace.technion.ac.il/events/instabilities-and-elastic-wave s-in-microstructured-soft-composites/ SUMMARY:Instabilities and Elastic Waves in Microstructured Soft Composites DESCRIPTION:Lecturer:Jian Li\n Faculty:Department of Aerospace Engineering\ n Institute:Technion – Israel Institute of Technology\n Location:Classro om 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n D etails: \n Abstract:\nUnderstanding of the mechanical behavior of soft com posites is essential for many research fields and applications such as ult rasound diagnostics\, vibration mitigation\, adhesives\, packaging materia ls\, and biological tissues. The properties of soft composites can be tail ored through designing their microstructures. Moreover\, thanks to the abi lity of soft materials to sustain large deformations\, their behavior can be tuned by deformations. Moreover\, large deformation induced elastic ins tabilities\, and associated dramatic structural and local material propert y changes\, can be utilized to design reconfigurable materials.\nIn this t alk\, we will start with examining elastic instability phenomena in variou s microstructured soft systems. We will first investigate the onset of ins tability in layered composites and 3D fiber composites. We will examine th e role of compressibility and fiber arrangement on the onset of instabilit y. Next\, we will discuss the domain formation and its transition to coope ratively wavy pattern via instabilities in soft particulate composites. We will show that these patterns can be tailored by altering the initial mic rostructural periodicity and concentration of the inclusions. Then\, we wi ll investigate the instability-induced pattern transformations in multipha se composites consisting of stiff inclusions and voids periodically distri buted in a soft matrix. Distinct patterns characterized by significantly d ifferent negative Poisson’s ratio (NPR) behaviors will be discussed\; mo reover\, we will show that the mechanical responses and auxetic behaviors can also be tuned by inclusion distribution. Finally\, we will illustrate an application of employing these reversible pattern transformations to ma nipulate elastic wave propagation. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-344@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190710T163000 DTEND;TZID=Asia/Jerusalem:20190710T173000 DTSTAMP:20230527T134947Z URL:https://aerospace.technion.ac.il/events/influence-of-pre-stressing-on- ballistic-shielding-efficiency/ SUMMARY:Influence of Pre-Stressing on Ballistic Shielding Efficiency DESCRIPTION:Lecturer:Dana Mendelson\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n The long-standing competition between advancing projecti les penetration power\, on one hand\, and increasing the efficiency of pro tective structures\, on the other hand\, has resulted in a very large body of scientific research along with engineering design methodologies. In th e latter context\, pre-stressing the target material is a commonly accepte d technology aiming at strengthening the resistance to projectile penetrat ion.\nThe present research aims at deriving a new and simple analytical mo del for assessing the effect of pre-stressing in improving the ballistic w orthiness of targets made of pressure sensitive solids like concrete or si ntered powder metals. Analysis is within framework of finite strain contin uum mechanics of elastoplastic solids\, and centers on the cavity expansio n field model.\nWe begin with a brief review of available studies (mainly experimental) on ballistic response of pre-stressed targets. Next\, we add ress the basic pattern of spherical cavity expansion under internal pressu re (simulating the projectile)\, in presence of remote confining pressure that induces the pre-stresses. New elegant solutions for the cavitation pr essure are derived\, reflecting the coupled effect of pre-stresses and pre ssure sensitivity. It is shown that compressive pre-stresses are indeed be neficial in increasing the ballistic velocity (in plate perforation) and d ecreasing the penetration depth (in deep penetration).\nThe underlying vie w in this approach (originally due to work by H. Bethe during WWII) is tha t the cavity expansion solution provides the specific cavitation energy ne eded to create a unit of new volume along the projectile path. Our solutio n has been facilitated by further simplifying assumptions of material inco mpressibility and perfectly plastic response. The alternative cylindrical cavitation field is analyzed as well\, and results are compared with those obtained from the spherical case.\nAnalytical findings are supported by a symptotic approximations and reduction to known solutions. We shall examin e sensitivities of the cavitation pressure to material parameters and leve l of confining pressure. Applications to ballistic perforation and penetra tion processes (assuming rigid projectiles and normal impact)\, and to des ign of protective structures\, will be discussed in view of model limitati ons and experimental results. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-325@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190724T163000 DTEND;TZID=Asia/Jerusalem:20190724T173000 DTSTAMP:20230527T132313Z URL:https://aerospace.technion.ac.il/events/thermodynamic-and-experimental -demonstration-of-inverted-brayton-cycle-in-heat-recovery-applications/ SUMMARY:Thermodynamic and Experimental Demonstration of Inverted Brayton Cy cle in Heat Recovery Applications DESCRIPTION:Lecturer:Idan Chazan\n Faculty:Grand Technion Energy Program\n Institute:Technion – Israel Institute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Det ails: \n A deregulated electricity supply market\, based on the implementa tion of renewable energy power plants\, vastly promotes the emerging “di stributed power generation” concept. Therefore\, numerous small and effi cient power units are progressively introduced to the market in order to s atisfy the new demands and replace large outdated power plants. Hence\, si gnificant potential lies in the further improvement of small-scale power p roduction technologies such as micro gas turbines\, especially in cogenera tion systems.\nThe presented work deals with increasing the efficiency of energy generation in decentralized energy supply through utilizing waste h eat. Waste heat typically contains one third of the total combustion energ y and is largely unused in contemporary small-scale power units. The curre nt effort investigates a new concept for the simultaneous production of ho t water and electrical energy\, based on the inverted Brayton cycle - expa nsion of hot exhaust gas at atmospheric pressure to sub-atmospheric condit ions\, extraction of heat in a recuperator and re-compression of the coole d gas back to atmospheric pressure. This heat recovery cycle generates pow er via expansion of the isobaric lines and can be used to drive an electri c generator\, while the heated coolant can be further used directly for co mbined heat and power generation.\nThe presentation will address the desig n and construction of a functional prototype where the inverted Brayton cy cle is experimentally demonstrated. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-327@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190729T163000 DTEND;TZID=Asia/Jerusalem:20190729T173000 DTSTAMP:20230527T132348Z URL:https://aerospace.technion.ac.il/events/a-laser-range-measurement-base d-terrain-following-concept-for-unmanned-aerial-vehicles/ SUMMARY:A Laser-Range-Measurement Based Terrain-Following Concept for Unman ned Aerial Vehicles DESCRIPTION:Lecturer:Arseny Livshitz\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n This seminar addresses the design\, error assessment an d analysis of a low cost\, adaptive\, laser range finder based\, terrain f ollowing system for unmanned aerial vehicles (UAVs). Such a system enables an aircraft to maintain a pre-defined vertical separation (altitude) over the terrain during flight. Terrain following is of interest in military a s well as civil applications with first papers on the subject dating back to the sixties of the previous century. Contemporary approaches are based primarily on radar and passive electro-optical sensors (cameras).\nIn this study a new approach is proposed to surmount the disadvantages of the pre vious systems and to provide a more compatible\, low cost terrain followin g solution for small UAVs. This system utilizes several\, rigidly mounted\ , laser range finders as its primary measurement device. The measurements obtained from the sensors are used to generate a desired terrain following trajectory for the aircraft. A trajectory tracking algorithm is then inco rporated to ensure that the aircraft remains on the desired path\, thus sa tisfying the required altitude. The complexity and performance of the prop osed system depends predominantly on the chosen layout of the sensors as w ell as other design parameters. The study discusses and thoroughly examine s the various error factors affecting the system performance. The goal is to develop an analytical error model for the system thus pinpointing the d ifferent factors which may cause either improvement or degradation in terr ain following performance as well as aid in the system design process. Fur thermore\, this study demonstrates the effect of the aircraft velocity on the terrain following performance and its relation to the terrain model. C onsequently\, a terrain model parameter identification scheme is developed and used to determine the preferred aircraft velocity.\nThe performance o f the adaptive terrain following system is evaluated using a three-dimensi onal Monte-Carlo simulation environment. The simulation results are used t o verify the analytical error model as well as to assess the performance o ver a varying terrain model. The resulting analytical error model quantifi es the overall system tracking error\, outlines the preferred values for v arious system parameters\, and mainly suggests the optimal pointing angle for the laser range finders. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-322@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190731T163000 DTEND;TZID=Asia/Jerusalem:20190731T173000 DTSTAMP:20230527T132211Z URL:https://aerospace.technion.ac.il/events/fabrication-and-optimization-o f-custom-fluorescent-tracer-particles/ SUMMARY:Fabrication and Optimization of Custom Fluorescent Tracer Particles DESCRIPTION:Lecturer:Meiran Miezner\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Commercial fluorescent tracer particles used for particl e image velocimetry are available in a very limited range of sizes and den sities\, and are prohibitively expensive for large-scale experiments. Ther efore\, a method for producing tracer particles with a wide range of densi ties and sizes\, in a robust and inexpensive way is highly desirable.\nIn this work\, we extend an earlier microfluidic system for tracer particle p roduction to a more stable\, pressure-driven operation\, and optimize the fluorescence and polydispersity of the resulting particles as a function o f chemistry and flow properties. We show that the density of the resultant particles is limited by chemistry\, whereas the size is limited by both c hemistry and flow. We examine the robustness and operating limits of the n ew system\, and validate the sufficiency of the fluorescent response of th e fabricated particles in a realistic experimental environment. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-328@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190821T163000 DTEND;TZID=Asia/Jerusalem:20190821T173000 DTSTAMP:20230527T132409Z URL:https://aerospace.technion.ac.il/events/study-of-the-physical-feasibil ity-and-stability-of-the-chapman-jouget-points-in-a-homogeneous-combustibl e-mixture/ SUMMARY:Study of the Physical Feasibility and Stability of the Chapman-Joug et Points in a Homogeneous Combustible Mixture DESCRIPTION:Lecturer:Irena Moshkovich Makarenko\n Faculty:Department of Aer ospace Engineering\n Institute:Technion – Israel Institute of Technology \n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom : \n Abstract: \n Details: \n The progress of a homogenous combustible mix ture wave can occur within two discreet combustion regimes\, deflagration and detonation. According to the literature\, it seems that there is no co nsent about the numerical value of those velocities\, although the experim ental conditions are the same. If we look at a burning wave (with SSSF con ditions)\, in horizontal channel\, we will find that the velocity of the m ixture that should enter the channel in order to keep the wave stable\, is not univalent. The range of the conservation equations solutions is a col lection of intersection points between the Raliegh and Hugoniot curves. Ac cording to the classical literature\, Chapman-Jouget suggested that the ta ngent point of those two curves determines the burning velocity in detonat ion and deflagration conditions.\nThis study examines theoretically all of those solutions\, using criteria such as thermodynamic stability\, mass a nd heat transfer and entropy growth. Trying to give a physical explanation to the great difference between the deflagration velocity determined by C hapman-Jouget and the burning velocity that was found experimentally. The mathematical solution proposed at this study\, is based on the Onsager the ory\, which links between the entropy growths phenomena. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-323@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190911T163000 DTEND;TZID=Asia/Jerusalem:20190911T173000 DTSTAMP:20230527T132229Z URL:https://aerospace.technion.ac.il/events/wind-tunnel-tests-to-investiga te-the-behavior-of-a-dual-lift-system/ SUMMARY:Wind Tunnel Tests to Investigate the Behavior of a Dual Lift System DESCRIPTION:Lecturer:Omer Fogel\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n In many cases helicopters carry external loads that are conn ected by slings to a hook on the fuselage (slung loads). The main advantag es of this method are the capability to transfer big loads and the ease of handling those loads. When the load is too heavy to be carried by a singl e helicopter\, a multi lift technique can be applied: Connecting a single load to the hooks of two (dual lift) or more helicopters. Dual lift presen ts a complex dynamic system. The possibility of dual lift was presented by limited flight tests and investigated by various numerical analyses. The present research will present the use of wind tunnel tests to investigate various aspects of dual lift operations.\nA rig has been designed and buil t to represent the helicopters hooks\, the suspension cables and the load below the hooks. The rig includes a bar\, where the tips of this bar repre sent the hooks of the two helicopters. During the wind tunnel tests each t ip can move along the bar axis\, thus representing changes in the distance between the two helicopters. In addition\, the pitch and yaw angles of th e bar can be changed during the test\, representing changes in the relativ e altitude and flight formation of the two helicopters. In the present stu dy the load is a model of a CONEX container with two stabilizing fins. A n umerical simulation of the test was also developed where the coupled dynam ics of the system (suspension cables and the slung load) is modeled. The s imulation includes the influence of aerodynamic\, gravity and inertia effe cts. Results of the wind tunnel tests will be presented. The test results will be compared with results of the numerical model. The validated numeri cal model will be used to study the influence of various parameters on the dual lift operation. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-324@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20190925T163000 DTEND;TZID=Asia/Jerusalem:20190925T173000 DTSTAMP:20230527T132254Z URL:https://aerospace.technion.ac.il/events/internal-ballistics-of-boron-c ontaining-solid-fuel-ramjet/ SUMMARY:Internal Ballistics of Boron Containing Solid Fuel Ramjet DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n The Ramjet engine is a simple air-breathing device with out any moving parts such as compressors or turbines. The basic idea behin d ramjet propulsion is aerodynamic compression of air\, making it suitable for supersonic flight speed. At Mach numbers of 2-4\, the ramjet is highl y efficient and has superiority over other types of engines.\nThe solid fu el ramjet (SFRJ) is the simplest type of a ramjet engine and it is charact erized by increased energy density\, simplicity\, relatively low cost and safety. The solid fuel combustor is made of a hollow cylinder of fuel\, wh ere air flows through its port and combustion takes place between the gasi fying fuel surface and the bulk airflow. A diffusive flame is established within the boundary layer over the solid fuel surface.\nMetal additives to the commonly used hydrocarbon fuels can provide better energetic performa nce\, especially for volume-limited systems. Boron exhibits remarkable the oretical energetic performance (40% more than hydrocarbons) with the highe st energy density of all elements\, about three times of hydrocarbon fuels . In order to realize these advantages\, the boron particles must ignite a nd combust completely within a limited time residence. However\, this is d ifficult since boron particles are initially coated with an oxide layer\, which inhibits combustion.\nThe present study focuses on modeling the comb ustion of the hydrocarbon solid fuel with boron particles.\nA 2-D axisymme tric model of a ramjet combustor\, at Mach 2.5 was solved numerically util izing the ANSYS FLUENT computational fluid dynamics (CFD) code. A series o f simulations were performed for various parameters such as flight altitud e\, fuel port diameter\, bypass ratio\, boron content and boron particle d iameter. The sensitivity of the SFRJ flowfield and the performance on the various parameters was studied. The results show a strong dependence of th e engine performance on particle initial diameter and after-burner length. CATEGORIES:Seminars END:VEVENT BEGIN:VEVENT UID:0-308@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191002T163000 DTEND;TZID=Asia/Jerusalem:20191002T173000 DTSTAMP:20230527T131617Z URL:https://aerospace.technion.ac.il/events/study-of-the-durability-of-aer onautical-structures-under-extreme-accelerations/ SUMMARY:Study of the Durability of Aeronautical Structures under Extreme Ac celerations DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n Elbit Systems Inc. is developing an autonomous drone fo r long range missions. In order to save time and to use electrical batteri es having short time power supply\, this drone is designed to be launched to its remote operation zone inside a 120 mm mortar shell. During the laun ch the pressure in the mortar barrel creates on the shell an acceleration pulse with a peak of about 10\,000 g within about 3 milliseconds. This wor k examines the durability of the designed drone having the extreme launch acceleration.\nThis work includes three steps. First\, the original design of Elbit was analyzed and approved to meet the geometrical and functional conditions while keeping its rigidity. Then\, based on this updated desig n and its CAD model\, a FEA model was built\, using the ANSYS Workbench so ftware package with the Explicit Dynamics (Autodyn) solver. In the second step the FEA model was calibrated and verified using drop tests results. T he drop tests were performed with a dummy mortar shell having an equivalen t FEA model and equipped with two accelerometers. A fast video camera was also used for redundancy and for measuring the impact velocities in the dr op tests. Those velocities were used as inputs for the ANSYS simulations\, and their acceleration results were compared to the accelerometers readin gs for the calibration of the numerical FEA model. Finally\, the calibrate d FEA ANSYS model was used to simulate the drone structure response to the forces acting on the mortar shell during its launch. The launch simulatio n results showed that most of the drone structure withstand the extreme ac celeration conditions during its launch inside the mortar shell. However\, the magnets of the selected COTS (Commercial Off-The-Shelf) propeller mot ors\, do not withstand these conditions and therefore these motors must be chanced or redesigned. In addition\, based on the FEA results\, it is rec ommended to strengthen some parts in the current design. CATEGORIES:Seminars END:VEVENT BEGIN:VEVENT UID:0-321@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191104T163000 DTEND;TZID=Asia/Jerusalem:20191104T173000 DTSTAMP:20230527T132149Z URL:https://aerospace.technion.ac.il/events/investigation-of-the-influence -of-graphite-additives-on-the-fuel-regression-rate-in-hybrid-propulsion/ SUMMARY:Investigation of the Influence of Graphite Additives on the Fuel Re gression Rate in Hybrid Propulsion DESCRIPTION:Lecturer:Silky Elanjickal\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n Hybrid propulsion can be a good alternative to the sol id and liquid propellant systems\; recently it has been the preferred choi ce for space tourism missions. In comparison to the solid and liquid prope llant systems\, hybrid rockets have improved safety and controllability. H owever\, one of the major drawbacks of hybrid motors is its slow regressio n rate leading to a low thrust. The main objective of this research is to experimentally and theoretically investigate the influence of an additive called expandable graphite (EG) on the fuel regression rate.\nExpandable g raphite (EG) has a unique property of forming accordion-like strings which are several times longer than the original particle size\, when heated to high temperatures. EG is known to have a high thermal conductivity. When mixed with a fuel matrix\, these strings can increase the heat transfer in to the fuel through conduction\, thus increasing the regression rate. Stat ic firing tests were conducted employing polymeric and liquefying fuels\, with and without EG\, using gaseous oxygen as the oxidizer. The experiment al results revealed an increase of 30%-200% in the fuel regression rate du e to the addition of EG into the fuel matrix. A larger relative effect was observed for the polymeric fuel in comparison to the liquefying fuel. The oretical model predictions showed good agreement with the experimental res ults\, within approximately ± 10%. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-319@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191106T163000 DTEND;TZID=Asia/Jerusalem:20191106T173000 DTSTAMP:20230527T132102Z URL:https://aerospace.technion.ac.il/events/plasma-propulsion-for-space-ap plications-technological-trends/ SUMMARY:Plasma Propulsion for Space Applications – Technological Trends DESCRIPTION:Lecturer:Dr. Dan Lev\n Faculty:Space Propulsion Systems Dept.\n Institute:Rafael - Advanced Defense Systems\n Location:Classroom 165\, gr ound floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n In the past two decades\, plasma propulsion for space applications has see n an increasing use for all types of satellites\, from hefty GEO communica tions satellites\, through tiny cubesats and to deep space missions. In pa rticular\, thanks to the propellant mass savings associated with using pla sma propulsion\, it is the leading candidate for communications satellite mega-constellations in low earth orbit\, such as those proposed by SpaceX and OneWeb. In addition\, the financial incentives in employing efficient plasma thrusters drove both industry and academia to develop new types of plasma thrusters. To date\, a myriad of technological subclasses of plasma propulsion exist\, each at a different Technological Readiness Level (TRL ).\nThe presentation will cover the basic aspects of plasma propulsion and present its physical concepts. The presentation will then focus on curren t technological trends with their implementation in contemporary space mis sions. Lastly\, the presentation will briefly present current developments at Rafael\, all focused on Hall thruster based propulsion systems. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-320@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191111T163000 DTEND;TZID=Asia/Jerusalem:20191111T173000 DTSTAMP:20230527T132126Z URL:https://aerospace.technion.ac.il/events/a-tale-of-two-experiments-in-u nsteady-and-turbulent-flows-boundary-layers-and-wind-turbines/ SUMMARY:A Tale of Two Experiments in Unsteady and Turbulent Flows: Boundary Layers and Wind Turbines DESCRIPTION:Lecturer:Asst. Prof. Duvvuri Subrahmanyam\n Faculty:Department of Aerospace Engineering\n Institute:Indian Institute of Science (IISc)\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \ n Abstract: \n Details: \n In this talk I'll present two experimental inve stigations where unsteady and turbulent flow physics form the common under lying theme.\nThe first study\, which is fundamental in nature\, was aimed at obtaining insights into the dynamics of non-linear scale interactions in a turbulent boundary layer. An active wall perturbation technique was u sed to apply external forcing to the flow in a targeted manner. This appro ach allowed for the transfer function(s) associated with interactions betw een specific scales (or modes) to be highlighted\, leading to an interesti ng set of observations with broad implications for turbulence modeling and flow control.\nThe second study\, which has a more applied flavor\, deals with the aerodynamics of vertical-axis wind turbine models at full dynami c similarity to field turbines. The use of compressed-air (up to 230 bar) as the working fluid in these experiments provided access to very high Rey nolds numbers that reach into the asymptotic regime for performance. Resul ts from this study greatly aid in modeling efforts and can guide design co nsiderations for practical turbines.\nAt the end I will also give a brief overview of the presently ongoing research activities in my group in the a rea of hypersonic flows. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-318@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191113T163000 DTEND;TZID=Asia/Jerusalem:20191113T173000 DTSTAMP:20230527T132043Z URL:https://aerospace.technion.ac.il/events/development-of-an-ultrasonic-m ethod-for-measuring-the-ablation-rate-and-temperature-distribution-within- a-silica-phenolic-thermal-protection-material/ SUMMARY:Development of an Ultrasonic Method for Measuring the Ablation Rate and Temperature Distribution within a Silica-Phenolic Thermal Protection Material DESCRIPTION:Lecturer:Aleksander Zibitsker\n Faculty:Department of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Loc ation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n A bstract: \n Details: \n Re-entry and hypersonic vehicles\, as well as rock et motors\, are exposed to extreme heat loads\, shear forces and chemicall y aggressive gasses. To protect the structure of the vehicle\, ablative th ermal protection system (TPS) materials are commonly used.  As these mate rials protect the vehicle\, they sacrifice themselves and\, as a result\, change in thickness and shape. This adversely affects the insulation and a erodynamic performance of the vehicle.  Hence\, during testing and certif ication of ablative TPS materials it is critical to monitor their ablation performance. The main objective of the current research is to use an ultr asonic technique to monitor the material ablation process of silica-phenol ic TPS material. Moreover\, due to the large temperature gradients within the material\, a method for correction of temperature influence on speed o f sound was sought after.\nMany ablative TPS materials\, including silica- phenolic\, have anisotropic structure\, which causes a diffuse backscatter of ultrasonic pulses propagating through the material.  Since these ultr asound reflections come from the internal material micro-structure\, they are received earlier than the echo from the ablating surface. Thus\, they can be used to correct the decrease in speed of sound as the material temp erature rises.\nThe current study will show how monitoring the temperature dependent behavior of the backscattered echoes was used to correct the sp eed of sound (SOS) change in the material. Additionally\, based on the exp erimental measurements of the SOS temperature dependence\, evaluation of t ime-varying temperature profiles within the material will be presented. Th e performance of the developed method is evaluated based on several ablati on experiments using an oxy-acetylene torch apparatus. Verification of the developed method is based on post-test micro-CT and ultrasound scans of t he ablated samples. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-307@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191120T163000 DTEND;TZID=Asia/Jerusalem:20191120T173000 DTSTAMP:20230527T131558Z URL:https://aerospace.technion.ac.il/events/consensus-based-cooperative-gu idance-laws-for-simultaneous-target-interception/ SUMMARY:Consensus-Based Cooperative Guidance Laws for Simultaneous Target I nterception DESCRIPTION:Lecturer:Benjamin Zadka\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Guiding a team of pursuers to simultaneously intercept a target (Salvo-attack) is crucial when dealing with modern target defenses . The main objective of the current research is to develop cooperative gui dance geometrical rules to achieve simultaneous interception of a stationa ry target by a team of heterogeneous pursuers\, modelled with non-linear u nicycle kinematics.\nWe will begin the talk with an introduction and an ov erview of existing impact time guidance laws. This will be followed by the presentation of the proposed cooperative geometrical rules that lead to s imultaneous interception. The interception can occur either in the minimum possible time or in any larger desired impact time. For the minimum possi ble impact time geometrical rule\, the communication topology between the pursuers follows a cyclic pursuit framework. For the desired impact time g eometrical rules\, the communication topology follows a leader-follower fr amework\, where the leader imposes the desired impact time independent of the other pursuers in the system\, and the followers modify their impact t imes according to that of the leader.\nFinally\, guidance laws to enforce the proposed geometrical rules will be introduced\, while also taking into account heading errors. Simulation results will be presented during the t alk to exemplify the theoretical results. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-311@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191127T163000 DTEND;TZID=Asia/Jerusalem:20191127T173000 DTSTAMP:20230527T131722Z URL:https://aerospace.technion.ac.il/events/performance-study-of-low-cost- rocket-controlled-by-solenoid/ SUMMARY:Performance Study of Low-Cost Rocket Controlled by Solenoid DESCRIPTION:Lecturer:Benny Begun\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Currently\, among aerospace industries\, there is an increa sing demand for advancements in rocket precision. Although these systems h ave provided great technological advancement in this arena\, they are acco mpanied by high costs and complex mechanisms.\nOne of the most common cont rol systems that are used in ammunition systems is the Servo. Despite its common usage\, the mechanical complexity and high costs are of disadvantag e to aerospace industries.\nAs a result of the challenges associated with the Servo system\, a considerable amount of research has been devoted to o btaining an alternative solution.\nThe main objective of the current resea rch is to propose a unique method to control a rocket which will strike th e balance between precise performances and the cost of the rocket.\nWe wil l begin the talk with an introduction and an overview of the current state concerning precise rockets. This will be followed by proposing a new guid ance law based on Vector Guidance law which leads to more robust rocket pe rformances while requiring low acceleration commands.\nAlso\, a unique act uating system driven by solenoids that are controlled by a PWM controller will be shown.\nFinally\, the complete rocket configuration will be introd uced. Simulations results will be presented during the talk to exemplify t he results CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-313@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191204T163000 DTEND;TZID=Asia/Jerusalem:20191204T173000 DTSTAMP:20230527T131802Z URL:https://aerospace.technion.ac.il/events/cathodic-arc-plasma-actuator-f or-flow-manipulation/ SUMMARY:Cathodic Arc Plasma Actuator for Flow Manipulation DESCRIPTION:Lecturer:Anton Ronis\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Flow separation is an important phenomenon to consider when designing airplane wings\, stabilizers\, and other fluid dynamics applica tions such as ground vehicles and internal diffuser flows. When unattended flow separation can lead to increase in drag\, stall and energy losses\, up to a loss of controlled flight. It is therefore desirable to have actua tors and associated control techniques that can mitigate this phenomenon\, a research domain collectively known as flow control.\nIn this work we ch aracterize the performance of a novel plasma actuator\, termed as the cath odic arc actuator (CAA). The CAA operates by igniting a cathodic-arc disch arge between two closely spaced flush electrodes. The discharge time evolu tion was experimentally characterized using several techniques including: fast photography\, spectroscopy\, particle image velocimetry (PIV)\, as we ll as direct measurement of thrust. In the first part of the talk we prese nt a time dependent 0-D thrust model of the CAA interaction with ambient a ir. The model is shown to be in excellent agreement with measurement resul ts.\nIn the second part of the talk we present results from a flow control experiment\, where the CAA is embedded in an aerodynamic model and operat ed inside a low speed wind tunnel. Hot wire anemometry and optical-oil bas ed techniques were used to measure the influence of actuator operation on the flow. A procedure for selecting aerodynamic model parameters for such experiments will be discussed as well. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-312@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191209T163000 DTEND;TZID=Asia/Jerusalem:20191209T173000 DTSTAMP:20230527T131742Z URL:https://aerospace.technion.ac.il/events/rate-limiting-constrains-in-ph ase-change-materials-pcm-for-miniature-aircraft-propulsion-systems/ SUMMARY:Rate Limiting Constraints in Phase-Change-Materials (PCM) for Minia ture Aircraft Propulsion Systems DESCRIPTION:Lecturer:Matan Feldman\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Micro Aerial Vehicles (MAV) require extremely lightweight propulsion systems. Whereas most current MAV use electric batteries as po wer sources\, the presented work examines the possibility of using Phase-C hange Materials (PCM) as part of an alternative propulsion system. The pro posed power plant involves a rapid depressurization of cryogenic fluids fr om a stable liquid state to create vapor nuclei (bubbles)\, followed by nu clei growth till they coalesce\, forming a continuous vapor phase which is heated by the surroundings and later drive a micro-turbine. The transform ation rate from liquid to vapor plays a prominent role in the system\, and the limiting transition rates of several materials are investigated in te rms of their initial temperature and pressure\, as well as of the dimensio ns of the orifice through which they exit.\nA theoretical parametric analy sis of these impacts will be thoroughly reviewed\, introducing the homogen eous and heterogeneous nucleation rates (according to several theories) al ongside the correlating depressurization rates necessary to achieve them\; as well as demonstrating the applicability of such propulsion systems to propel a MAV by evaluating their outputs\, such as specific energy\, speci fic power\, possible mission time and total mass. The system combinations that provide the minimal specifications will be exhibited\, with a focus o n Hydrogen and Neon - which were found to be the most promising substances per unit of mass and volume\, respectively. Comparison with electric batt eries will be presented. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-315@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191211T163000 DTEND;TZID=Asia/Jerusalem:20191211T173000 DTSTAMP:20230527T131945Z URL:https://aerospace.technion.ac.il/events/the-impact-of-fuel-composition -on-flame-holding-in-a-scramjet-combustor/ SUMMARY:The Impact of Fuel Composition on Flame Holding in a Scramjet Combu stor DESCRIPTION:Lecturer:Haim Elya Brod\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac t: \n Details: \n Scramjet engines are an effective hypersonic propulsion\ , as they breath air at hypersonic speeds and slow it down to supersonic s peeds in the combustor\, allowing for effective heat addition.  Liquid fu eled scramjet allow for several benefits\, including using the fuel in a h eat exchanger as heat sink for the structure of the engine. As fuel passes the heat exchanger it will undergo endothermic reaction\, producing mainl y Ethylene and Methane. In this research we looked at the effect of those fuels composition on the supersonic combustion.\nWe designed and used a ne w experimental setup for scramjet combustor. A hydrogen air heater and a c onverging diverging nozzle are used to obtain vitiated air with a stagnati on temperature of about 1600 K\, stagnation pressure of 12 bar and a Mach number of 2.2 at the combustor inlet. A cavity is used for flame stabiliza tion\, and the fuel is injected through two ports – in the cavity and up stream of the cavity. The diagnostics include static pressure measurements along the walls\, as well as CH chemiluminescence and shadowgraph imaging . The results presented herein show the impact of fuel flow rate and fuel composition on the flame holding\, flame location\, flow field\, and press ure distribution in the combustor. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-317@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191216T163000 DTEND;TZID=Asia/Jerusalem:20191216T173000 DTSTAMP:20230527T132025Z URL:https://aerospace.technion.ac.il/events/multiscale-instabilities-in-ac tive-elastomers/ SUMMARY:Multiscale Instabilities in Active Elastomers DESCRIPTION:Lecturer:Artemii Goshkoderia\n Faculty:Department of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Loca tion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Ab stract: \n Details: \n We study magnetomechanical instabilities in magneto active elastomer (MAE) composites undergoing finite strains in the presenc e of a magnetic field. In particular\, we consider MAE composites with cha in-like microstructure. We analyze the influence of the applied magnetic f ield along the chains on the stability of the MAE composites at both micro scopic and macroscopic length scales. To this end\, we develop a numerical scheme to detect the onset of instabilities at the long wave and finite l ength-scales. By applying the developed numerical technique\, we analyze t he influence of the materials microstructure geometrical parameters and ap plied magnetic field on the onset of instabilities in soft MAEs.\nWe found that identical MAE composites with periodically distributed particles can switch to a variety of new patterns with different periodicity under part icular levels of the applied magnetic field. The post buckling analysis is performed to numerically realize the newly formed patterns dictated by th e magnitude of the applied magnetic field. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-310@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191218T163000 DTEND;TZID=Asia/Jerusalem:20191218T173000 DTSTAMP:20230527T131702Z URL:https://aerospace.technion.ac.il/events/using-optimization-process-to- determine-aircraft-configuration-in-the-conceptual-design-phase/ SUMMARY:Using Optimization Process to Determine Aircraft Configuration in t he Conceptual Design Phase DESCRIPTION:Lecturer:Shay Arzi\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n The early phases of a new project are the optimal time to per form major changes in the design configuration. The cost of such changes a t these stages is minimal while the ability to perform them is high. For t his reason\, conducting a productive conceptual design phase is very impor tant.\nThis study presents a method for improving the conceptual design ph ase at the beginning of a new aircraft project. The method is constructed of a multi-disciplinary design optimization program combined with a sugges ted work process to enable a more productive conceptual design phase. The optimization program enables to perform initial analysis of many aircraft configurations in order to better understand the design space. The program is given the aircraft requirement set as an input (required speed\, requi red range\, ...) and performs initial evaluation of various analysis inclu ding geometry\, aerodynamic\, weight\, propulsion and performance. The pro gram enables to estimate the value of many aircraft designs and allow the user to better understand the design space before choosing a preferred ini tial design configuration. With the use of the optimization program and th e suggested work process\, a user can better define a preferred design con figuration to best meet the project requirements. After using the program\ , the engineering team can initiate the program with a better design that will enable to shorten the iteration process. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-309@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191224T163000 DTEND;TZID=Asia/Jerusalem:20191224T173000 DTSTAMP:20230527T131641Z URL:https://aerospace.technion.ac.il/events/harnessing-aerospace-technolog y-for-power-and-renewable-energy-production/ SUMMARY:Harnessing Aerospace Technology for Power and Renewable Energy Prod uction DESCRIPTION:Lecturer:Dr. Eldad Avital\n Faculty:School of Engineering and M aterials Science\n Institute:Queen Mary University of London UK\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra ct: \n Details: \n In this talk\, we will look at recent computational dev elopments of fluid-structure interaction (FSI) simulations and aerodynamic design for power production in aerospace and renewables. The approach of coupling a turbulent flow solver as Large Eddy Simulation (LES) with a str uctural dynamics solver will be described by joining the finite volume met hod (FVM) with the combined finite element method-discrete element method (FEM-DEM). The coupled FSI approach will be deployed to study power genera tion from kinetic turbines of low speed aerodynamics to hydrogen fusion re actors of high speed aerodynamics and non-linear acoustics.\nIn the second part of the talk\, we will look at a recent aerodynamic blade design meth od to delay stall and reduce tonal noise. Other passive control means as m icro vortex generators and Gurney flaps will be discussed for turbomachine ry and kinetic turbines applications. The talk will conclude with a short discussion on supersonic jet noise and associated non-linear acoustics. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-297@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191225T163000 DTEND;TZID=Asia/Jerusalem:20191225T173000 DTSTAMP:20230527T131159Z URL:https://aerospace.technion.ac.il/events/influence-of-the-slings-on-the -dynamics-of-slung-load/ SUMMARY:Influence of the Slings on the Dynamics of Slung Load DESCRIPTION:Lecturer:Matan Steiner\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n Transportation of external loads by helicopters is very c ommon and is used for a fast transfer of large loads to places that are ha rdly accessible by other means. In these cases\, the load is connected to the bottom of the helicopter by slings. During flight\, the load is subjec ted to aerodynamic forces and moments that cause it to oscillate and to ro tate about its vertical axis.\nDue to the rotation\, the slings twist and wind together to form a helical ply structure. The winding of the slings c reates a torque that opposes the rotation\; as a result\, the rotation slo ws down\, stops and then a rotation in the opposite direction develops (un winding). This periodic motion is difficult to model\, not only because of the complex aerodynamics of the torsional moment (autorotation)\, but als o because of the difficulty in modeling the cables periodic winding and un winding and predicting the torque that the slings apply on the rotating lo ad. The present research deals with the latter torque\, which is a superpo sition of the torque induced by the torsional rigidity of each of the slin gs\, and the torque induced by changes of the slings spatial geometry as a result of the rotation of the load.\nRopes are complex structures and the ir mechanical properties are affected by many factors. An empirical model for the torsional rigidity of the ropes is presented. This model includes the influence of tension\, number of rotations in each direction\, and hys teresis. The empirical model is used to describe four different kinds of r opes and is verified by various tests that include different combinations of tensions and torsion histories.\nThe model of the torque induced by cha nges of the slings spatial geometry as a result of the rotation of the loa d is derived using energy methods. The solution includes two different reg ions: cases where the ropes are not in contact with each other and cases w here the ropes are in contact and wind together to form a ply structure.\n The coupled model is verified by comparisons of its results to detailed te sts that include  different magnitudes of the load rotation angle and dif ferent load weights. The verified model is used for parametric studies. Fi nally\, the dynamic rotation of the load is modeled and solved. The deriva tion includes the effects of friction between the ropes and damping caused by each rope. The solution is verified for the four types of ropes and fo r different load weights and moments of inertia. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-314@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20191230T163000 DTEND;TZID=Asia/Jerusalem:20191230T173000 DTSTAMP:20230527T131926Z URL:https://aerospace.technion.ac.il/events/mitigation-of-combustion-insta bilities-by-local-diluent-gas-in-a-lean-premixed-swirl-stabilized-combusti on-systems/ SUMMARY:Mitigation of Combustion Instabilities by Local Diluent Gas in a Le an Premixed Swirl-Stabilized Combustion Systems DESCRIPTION:Lecturer:Nikhil Balasubramanian\n Faculty:Department of Aerospa ce Engineering\n Institute:Technion – Israel Institute of Technology\n L ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n A major motivation for research in combustion sc ience and technology is to reduce emissions from power plants\, large scal e industrial furnaces\, automobiles\, aircrafts\, etc. Development of low emission gas turbines has placed a great demand for novel methodologies fo r emission control\, without compromising power production.\nLean premixed combustion systems emerged as a viable solution to the problem\, and has been successfully implemented in stationery gas turbine based energy produ ction units\, meeting the same energy demands and reducing  emissions to single digit ppm levels. Premixed combustion systems offer better control over the flame temperature\, which is directly linked to and CO emissions. \nHowever\, premixed combustion systems are susceptible to combustion inst abilities\, which is the coupling between heat release\, pressure and flow acoustics\, which can lead to high amplitude pressure oscillations. These oscillations can cause severe damage to the combustor hardware and flame flashback.\nSuccessful prediction of thermo-acoustic instabilities is chal lenging due to the complex flow phenomena\, unsteady heat release and unde fined acoustic boundaries.\nWe built a fully premixed experimental swirl s tabilized combustion system at the Fine rocket propulsion center to analyz e the effect of injecting dilution gases in specific regions of the combus tor as a way to reduce combustion instabilities. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-316@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200101T163000 DTEND;TZID=Asia/Jerusalem:20200101T173000 DTSTAMP:20230527T132006Z URL:https://aerospace.technion.ac.il/events/fiber-optics-based-aeroelastic -shape-sensing/ SUMMARY:Fiber-Optics-Based Aeroelastic Shape Sensing DESCRIPTION:Lecturer:Miko Keren Rattner\n Faculty:Department of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abs tract: \n Details: \n In recent years\, flight vehicles are becoming progr essively more elastic and as a result\, aeroelastic phenomena are becoming more prominent. A gusty environment or a high-load maneuver can result in considerable static or dynamic aeroelastic response\, which\, without pro per control\, might lead to excessive loads or even failure. Hence\, there is a great incentive to sense\, quantify\, and control aeroelastic respon ses. Static shape sensing can be used to monitor the elastically deformed shape of a vehicle in trimmed flight\, while dynamic shape sensing can be used to identify the aeroelastic system (frequencies and damping) under th e aircraft's operational conditions and control it.\nThis study investigat es the methodology and application aspects of aeroelastic shape sensing us ing fiber-optic sensors in a dedicated wind-tunnel experiment. For that pu rpose\, an elastic wing was designed and manufactured using rapid prototyp ing. The wing was tested at the Technion’s subsonic wind-tunnel at subcr itical points and all the way to flutter. Strain measurements via both di screte and distributed dynamic fiber-optic sensing technologies were used to estimate a wing's deformed shape and modal displacements using a strain -to-displacement transformation algorithm.\nThe seminar will present the u se of optical fibers to measure strains\, and the strain-to-displacement a lgorithm used in this study. The seminar will present the test case\, aero elstic analyses\, and results from steady and dynamic wind-tunnel tests. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-300@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200106T163000 DTEND;TZID=Asia/Jerusalem:20200106T173000 DTSTAMP:20230527T131259Z URL:https://aerospace.technion.ac.il/events/sub-optimal-spatial-guidance-u nder-angular-constraint-in-aerodynamic-flight/ SUMMARY:Sub-Optimal Spatial Guidance under Angular Constraint in Aerodynami c Flight DESCRIPTION:Lecturer:Nahshon Indig\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract : \n Details: \n The purpose of the study is to develop optimal spatial gu idance-laws under terminal angular constraint in atmospheric flight\, whic h enable the pursuer to reach its target under various optimization object ives criteria (minimum time\, maximum velocity or minimum acceleration eff ort)\, using the traditional acceleration controller\, the thrust controll er or a combination of both. The research considers several guidance relat ed problems\, focusing on developing numerical\, empirical and analytical methods for analyzing and solving these problems. In this area of guidance laws with terminal angular constraint\, most of the existing studies have been performed under various accumulating assumptions (engagement geometr y is linearized\, the interceptor is near the collision course and the dyn amics are for a vacuum flight) which created a gap between the terms of th e studies and the real flight conditions.\nIn the first part\, a novel nea r optimal closed-loop guidance law is introduced with maximum velocity cri teria for the 2D nonlinear problem under terminal angular constraint (base d on the linear solution) with performances matching the optimal results v ery closely. In the second stage\, this law is extended to the spatial (3D ) case\, by determining the preferred spatial maneuver plane based on ener gy consideration.\nIn the second part\, the spatial problem with 'minimum- time' optimization objective criteria under terminal  angular manifold co nstraint (known as Dubbin’s problem) is solved. The study expands the pr oblem to a more difficult case: minimum time arrival with a terminal conic al manifold constraint and suggests a near-optimal closed-loop guidance ap proach to address the 3D problem with time-varying speed  and optimal clo sed-loop guidance approach for vacuum flight.\nIn the third part\, the fam ous Goddrad problem with various optimization objectives criteria is addre ssed\, where the controller is the thrust input that replaces the traditio nal acceleration controller. This is a known singular control problem. Suc h problems are usually characterized by solutions that are difficult to fo rmulate. Previous research generally showed partial solutions to the Godda rd problem. The proposed solution formulates the analytical thrust control ler in closed loop for various variations of 1D and 2D Goddard problems un der different trajectory bending laws. The proposed method can be implemen ted for other singular control problems in various branches of science.\nI n the fourth part\, the study is focused on the 2D non-linear problem unde r angular constraints and with various optimization objectives employing t wo controllers: the thrust controller and the acceleration controller. Thi s problem has been discussed minimally in the literature. The main innovat ion in this part is the emphasis of the improvement performances potential when using the two controllers in parallel. A convex Pareto curve (in two optimization objectives) including all optimal solutions is obtained. Add ing Leitmann’s test for necessary conditions for Pareto-Optimality enabl es to deepen the understanding obtained from the optimal solutions in this complicate case. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-301@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200108T163000 DTEND;TZID=Asia/Jerusalem:20200108T173000 DTSTAMP:20230527T131322Z URL:https://aerospace.technion.ac.il/events/guest-seminar-fast-and-highly- compressible-single-and-multi-phase-reacting-flows/ SUMMARY:Guest Seminar - "Fast and Highly Compressible Single- and Multi-Pha se Reacting Flows" DESCRIPTION:Lecturer:Dr. Yoram Kozak\n Faculty:Department of Aerospace Engi neering\n Institute:Texas A&M University\, College Station\, TX\, USA\n Lo cation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n High flow speeds and significant compressibility levels can be found in a wide range of single- and multi-phase reacting fl ows. These include various propulsion and energy conversion systems\, such as scramjet and detonation engines\, industrial explosions\, and differen t military applications.\nBetter understanding of these extreme flow regim es is possible by either experimentation or numerical modeling. The latter requires the development of novel modeling approaches capable of providin g high accuracy in these extreme regimes characterized by large spatial an d temporal variability.\nIn this talk\, several unique numerical and exper imental difficulties\, each associated with a different flow configuration of interest\, will be discussed. First\, the limitations of the classical Eulerian-Lagrangian formulation for multi-phase flow modeling under highl y compressible conditions will be presented. It is demonstrated that for h ighly compressible flows\, typical interpolation methods fail and a Weight ed-Essentially-Non-Oscillatory (WENO) interpolation can provide a superior alternative. This new formulation is then utilized to critically assess t he accuracy of the classical Particle Image Velocimetry (PIV) technique fo r flow characterization in gas-phase detonations and high-speed turbulence . Also\, newly developed numerical techniques and models for liquid spray and solid particle combustion will be discussed. Then\, the dynamics of hi ghly compressible\, fast\, turbulent flames capable of undergoing a transi tion to a detonation wave are studied using Direct Numerical Simulations ( DNS) based on realistic experimental conditions. The results raise questio ns regarding the ability of the classical RANS and LES techniques to model properly the complex physics associated with these inherently unstable fa st turbulent reacting flows.\nFinally\, future research directions in the context of the problems discussed above will be presented. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-306@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200113T163000 DTEND;TZID=Asia/Jerusalem:20200113T173000 DTSTAMP:20230527T131534Z URL:https://aerospace.technion.ac.il/events/aeroelastic-system-data-analys is-using-the-hilbert-huang-transform/ SUMMARY:Aeroelastic System Data Analysis Using the Hilbert-Huang Transform DESCRIPTION:Lecturer:Ramya Raman\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Aeroelastic responses\, such as accelerations measured in f light\, are non-stationary signals in which the frequency content varies w ith flight speed and\, therefore\, in time. Aeroelastic responses might al so be nonlinear due to large structural deformations (in very flexible con figurations)\, structural free-play (e.g.\, in control surfaces)\, nonline ar aerodynamic forces (e.g.\, in transonic flight)\, or due to a very larg e excitation (e.g.\, in-store ejection). The objective of aeroelastic data analysis is to obtain an accurate representation of the dynamics of the n on-stationary nonlinear system. The current research study explores and co mpares several time-frequency methods for non-stationary nonlinear data an alysis\, including the Short-time Fourier transform (STFT)\, Wavelets\, an d the Hilbert-Huang Transform (HHT)\, with emphasis on the latter.\nIn the current research study\, the various time-frequency analysis methods were applied to aeroelastic response data of a wing obtained from computation and a wind-tunnel test. The computational data included accelerations due to gust excitation in multiple velocities. The wind tunnel data included a ccelerations measured at various speeds\, all the way to flutter. The data were analyzed using the above-mentioned signal processing techniques. Tim e-frequency responses are presented as Energy spectrum’s namely\, Spectr ogram\, Scalogram\, and HHT Spectrum (for the STFT\, Wavelets\, and HHT\, respectively). These time-frequency graphs provide insight into system ide ntification and change in frequency content with time\, as the airspeed is increased. All three techniques yielded similar results when the data was analyzed for multiple velocities. However\, precise details were obtained with Scalogram and HHT spectrum when the data were analyzed for individua l speeds. Additionally\, damping ratios were calculated using HHT amplitud e energies and power spectral densities\, which provided the damping ratio of the stable and unstable modes for multiple velocities until flutter. T he advantages and shortcomings of different techniques are discussed in th e test cases. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-296@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200115T163000 DTEND;TZID=Asia/Jerusalem:20200115T173000 DTSTAMP:20230527T131140Z URL:https://aerospace.technion.ac.il/events/electric-control-of-the-burnin g-rate-of-a-solid-propellant/ SUMMARY:Electric Control of the Burning Rate of a Solid Propellant DESCRIPTION:Lecturer:Inna Zamir\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Solid propellant rocket motors are simple\, easy for handlin g\, and ready for immediate operation. That is why they are the preferred rocket motors in multiple applications and missions. However\, in practice \, solid propellant motor thrust cannot be controlled once the propellant has been ignited. The thrust developed during operation depends on the pro pellant burning surface and burning rate. The burning surface may change a ccording to a predesigned geometry of the propellant grain\, but cannot be actively controlled during the propellant combustion. This research inves tigates the possibility of controlling the burning rate by applying electr ic field/voltage.\nCommon ammonium perchlorate (AP) based propellant were found to be insensitive to electric field. However\, the research revealed that ammonium nitrate (AN) based propellants are sensitive to electric ef fect\, and their burning rate can be controlled by applying voltage on the propellant. These findings are promising for better managing the energy a nd maneuverability of tactical motors\, as well as for small space motors\ , where such electric controlled solid motors may replace the traditional hydrazine motors\, whose use is projected to diminish and even to be banne d due to the hydrazine carcinogenic and toxic properties.\nAn experimental system has been designed\, constructed and tested. The experiments invest igated the effect of voltage (up to 250V) for different values of oxidizer mass fraction\, strand thickness\, storage condition\, and pressure\, dem onstrating 3-5 fold increase of the burning rate when increasing the volta ge from 70 to 200V. A theoretical model showed good agreement with the exp eriments. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-295@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200120T163000 DTEND;TZID=Asia/Jerusalem:20200120T173000 DTSTAMP:20230527T131124Z URL:https://aerospace.technion.ac.il/events/the-bar-itzhack-navigation-sem inar-pnt-research-at-the-osu-college-of-engineering-an-overview/ SUMMARY:The Bar-Itzhack Navigation Seminar - PNT Research at the OSU Colleg e of Engineering: an Overview DESCRIPTION:Lecturer:Prof. Dorota A. Grejner-Brzezinska\n Faculty:College o f Engineering\n Institute:The Ohio State University\n Location:Classroom 1 65\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Detai ls: \n A brief overview of the Ohio State College of Engineering (COE) wil l be presented\, with the emphasis on the strategic research pillars and t he research strengths and priorities. The focus will be on the COE’s res earch centers that form the operational core of the COE’s research missi on. The opportunities for collaborative research will be briefly discussed . In addition\, a newly established SMART Center at the OSU’s Transporta tion Research Center will be discussed to offer some insights into smart m obility and autonomy research and the COE’s capabilities in the area of autonomous vehicle testing.\nNext\, an overview of research in broad areas of Positioning\, Navigation and Timing (PNT) performed at COE\, with the emphasis on the research program of the Satellite Positioning and Inertial Navigation (SPIN) Lab\, will be discussed. Over the past 15+ years\, SPIN Lab has completed over 60 research projects sponsored by the Federal and State governments and the industry\, with a total budget of over $22M. The primary areas of research are GPS/GNSS algorithms\, mainly high-accuracy static and kinematic network-based solutions including the PPP technique\, GNSS error modeling\, and GNSS integration with inertial technology. As t he demand for ubiquitous navigation has been steadily growing\, alternativ e navigation methods based on multi-sensor systems with increasingly uncon ventional techniques\, such as Artificial Intelligence (AI)-based\, image and terrain-based solutions started to dominate SPIN Lab’s research port folio over the last more than a decade. More recently\, collaborative navi gation combined with the image-based approach and AI techniques has been t he driving force of the SPIN Lab’s research\, as these technologies are expected to support the key emerging applications\, such as autonomous veh icles\, UAS swarms\, indoor and transitional navigation\, and general mobi lity in smart cities\, etc. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-293@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200121T163000 DTEND;TZID=Asia/Jerusalem:20200121T173000 DTSTAMP:20230525T085423Z URL:https://aerospace.technion.ac.il/events/investigation-of-electric-prop elled-aircraft-performance/ SUMMARY:Investigation of Electric Propelled Aircraft Performance DESCRIPTION:Lecturer:Michael Dror Cossenas\n Faculty:Department of Aerospac e Engineering\n Institute:Technion – Israel Institute of Technology\n Lo cation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n With increasing use of electric-powered aircraft\ , there is a need for accurate mission planning tools. Electric aircraft d iffer from conventional ones in a few aspects\, most notably in the effici ency with which the energy they carry on board is converted into the mecha nical one. Expressing the efficiency of the electrical propulsion system a s the product of the efficiencies of its constituents (battery\, controlle r\, motor and propeller)\, semi-empirical models are suggested for each on e of them. They served as the basis for a mission planning tool that demon strated good accuracy when compared to the actual flight performance. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-298@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200122T163000 DTEND;TZID=Asia/Jerusalem:20200122T173000 DTSTAMP:20230527T131223Z URL:https://aerospace.technion.ac.il/events/guest-seminar-planes-of-future -past-dan-raymers-advanced-aircraft-designs-at-rockwell-lockheed-rand-and- crc-dr-dan-raymer/ SUMMARY:Guest Seminar: Planes of Future Past: Dan Raymer’s Advanced Aircr aft Designs at Rockwell\, Lockheed\, RAND\, and CRC - Dr. Dan Raymer DESCRIPTION:Lecturer:Dr. Dan Raymer\n Faculty:President\n Institute:Concept ual Research Corporation\n Location:Auditorium 235\, second floor\, Aerosp ace Eng.\n Zoom: \n Abstract: \n Details: \n Subject: Futuristic Aircraft Designs and a look at how big companies develop them.\nBenefit: Fun and ed ucational\, aimed at the airplane enthusiast crowd. No equations or calcul ations\, just lots of drawings and pictures of wild airplanes.\nDescriptio n: This talk by noted designer Dan Raymer covers his early involvement in the projects that became the X-31\, B-2\, F-22\, F-35\, and more. Raymer d escribes how and why these projects began. Then he shows his original base line design concepts and explains how they were created\, what was learned from them\, and what happened in the end. Raymer will also show one of hi s newer\, wilder designs called Sparky Flapjack. This is an electric super -STOL designed for "pocket airports."\n[gallery columns="2" link="file" s ize="medium" ids="17254\,17252"] CATEGORIES:Seminars LOCATION:Auditorium 235\, second floor\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-371@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200127T123000 DTEND;TZID=Asia/Jerusalem:20200127T133000 DTSTAMP:20230527T140148Z URL:https://aerospace.technion.ac.il/events/multispectral-infrared-thermog raphy-of-unknown-emissivity-targets/ SUMMARY:Multispectral Infrared Thermography of Unknown-Emissivity Targets DESCRIPTION:Lecturer:Iliya Romm\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Many industrial and scientific applications require accurate measurement of radiation flux emitted by target surfaces. One of its most important applications is thermal infrared imaging for non-contact measur ement and monitoring of temperature.\nEmitted radiation flux is a function of the object’s temperature (via the Planck equation) and of its radiat ive properties (emissivity). When the emissivity of an observed object is not sufficiently known\, the problem of temperature/emissivity separation (TES) is encountered. TES is perhaps the biggest challenge in infrared the rmography\, manifesting as an inability to decouple the effect of emissivi ty on the radiant flux\, and in following\, reliably recover temperature. Multispectral radiation thermometry (MRT) methods try to overcome this pro blem by assuming an emissivity model and combining measurements from sever al spectral bands to yield the target temperature and model parameters.\nT his research advances the state of the art in two avenues: by exploring be tter ways to operate MRT systems\, and by presenting an automated methodol ogy for their spectral design.\nIn terms of operation\, experimental pract ices for removing parasitic heat flux and random electronic noise are disc ussed. Image fusion is shown to serve a dual purpose: both overcoming dete ctor nonlinearities\, and increasing tonal fidelity. The commonly-used NUC (nonuniformity correction) procedure is challenged and improved upon. An extended optical system calibration procedure is suggested\, which capture s not only the relation between temperature and detected signal\, but also between temperature and the drift of the characteristic wavelength. Lastl y\, a mathematical model is developed for utilizing the new calibration te chnique in temperature recovery.\nIn terms of spectral design\, this work presents the first use of a multi-heuristic a-posteriori optimization tech nique for design space exploration of MRT systems. Automated designs can b e made applicable to either wider or narrower ranges of target emissivitie s\, via user-supplied information. Superiority of automated over manual de signs is demonstrated. Simulations indicate that a 4-channel thermographic system\, designed and operated according to the suggested guidelines\, ca n recover temperatures between 150-600°C within ±10°C for common aerona utical alloys (such as Inconel718\, HastelloyX and Ti-6Al-4V).\nThe indivi dual results of this work should all be seen as practical recommendations that can be applied to most contemporary MRT systems to improve their perf ormance with no hardware changes (with the exception of simple optical fil ter adjustment). CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-302@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200129T163000 DTEND;TZID=Asia/Jerusalem:20200129T173000 DTSTAMP:20230527T131345Z URL:https://aerospace.technion.ac.il/events/improved-time-reversal-methods -for-the-identification-of-flaws-in-aerospace-structures/ SUMMARY:Improved Time-Reversal Methods for the Identification of Flaws in A erospace Structures DESCRIPTION:Lecturer:Eyal Amitt\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Non-Destructive Testing (NDT) is one of the major requiremen ts in aerospace structural design. Appropriate use of NDT guarantees safet y in aerospace and is thus a subject of highest attention. In this study\ , a new model-based NDT method is proposed for damage identification. The computational inverse problem of identifying a scatterer in a time-depende nt wave field is considered. The wave speed of the background medium and t he wave source are assumed to be known. Wave measurements\, possibly noisy \, are given at chosen discrete points in space (sensor locations) and tim e. The goal is to find scatterer parameters such as location\, size and sh ape. The computational solution procedure consists of two steps. In the fi rst step\, a standard fast Arrival-Time Imaging (ATI) algorithm is employe d. This results in a rough image which provides possible regions for the l ocation of the scatterer. In the second step an optimization scheme based on Time Reversal (TR) is used to determine the location\, size and shape o f the scatterer.\nNext\, a comparison between combined ATI-TR and the well -known Full Waveform Inversion (FWI) method\, using the adjoint method as an efficient way to advance toward the real scatterer parameters\, is disc ussed. The goal of this study is to compare the performances of these meth ods with a focus on running time\, amount of data required and identificat ion capabilities. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-305@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200205T163000 DTEND;TZID=Asia/Jerusalem:20200205T173000 DTSTAMP:20230527T131509Z URL:https://aerospace.technion.ac.il/events/ablative-materials-screening-f or-solid-rocket-motors/ SUMMARY:Ablative Materials Screening for Solid Rocket Motors DESCRIPTION:Lecturer:Igor Sapozhnikov\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n The research investigates the effect of insulation fib er spatial orientation and aluminum content in the propellant composition\ , on particle erosion and thermochemical ablation.\nSolid propellants exhi bit self-sustained\, high-temperature combustion and generate large quanti ties of gaseous products. Composite propellants have been extensively used in the last 50 years. Metals such as aluminum are added to increase densi ty and total heat of combustion.\nIn solid rocket motors\, charring ablati ve materials function as heat barriers that protect the motor case through the mechanism of ablation. When exposed to heat\, they undergo an endothe rmic decomposition process. In solid rocket motor applications\, case insu lations based on Ethylene Propylene Diene Monomer and Kevlar are commonly used.\nIn the present research\, a subscale solid motor was used\, with an AP/HTPB/Aluminum based solid propellant. Seven static firing tests (six w ith low aluminum content and a single test with high content) were  condu cted successfully. The tested insulations had four different Kevlar reinfo rcing fibers orientations\; circumferential\, longitudinal\, diagonal and random. Examination and comparison of the test results enabled to reach th e conclusion that the longitudinal oriented fiber model had the largest ma ss loss.\nA numerical model of the solid motor with the ablative insulatio n was incorporated. The measured values of chamber pressure and motor case temperature in the static firing tests served as boundary conditions. The convective and radiative heat flux from the gases transferred to the insu lation were evaluated with empirical correlations. The numerical results w ere compared to the experimental with low Al propellant content and exhibi ted slight overprediction. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-43@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200304T090000 DTEND;TZID=Asia/Jerusalem:20200304T100000 DTSTAMP:20221030T083446Z URL:https://aerospace.technion.ac.il/events/the-60th-israel-annual-confere nce-on-aerospace-sciences-iacas/ SUMMARY:The 60th Israel Annual Conference on Aerospace Sciences (IACAS) DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Dan Panorama H otel Tel Aviv & Technion\, Haifa\n Zoom: \n Abstract: \n Details: The 60th IACAS will take place on:\nMarch 4\, 2020 – Dan Panorama Hotel\, Tel Av iv\, Israel\nMarch 5\, 2020 – Technion Campus\, Haifa\, Israel\nThe Isra el Annual Conference on Aerospace Sciences\, spanning several generations\ , is celebrating its 60th year !\nThe conference is an important annual ev ent on the calendar of the aerospace community in Israel and arouses a g reat deal of interest abroad. Taking part in this yearly event are enginee rs\, scientists and experts in the field of aeronautics and astronautics \, representing well-known local aerospace agencies and industries\, as w ell as participants from major research centers worldwide.\nThe two day c onference covers new research\, presents up-to-date technology and provide s a forum for exchanging new ideas.\n \;\n CATEGORIES:Events LOCATION:Dan Panorama Hotel Tel Aviv & Technion\, Haifa END:VEVENT BEGIN:VEVENT UID:0-65@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200304T090000 DTEND;TZID=Asia/Jerusalem:20200305T090000 DTSTAMP:20221031T095955Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%9b%d7%a0%d7%a1-%d 7%94%d7%99%d7%a9%d7%a8%d7%90%d7%9c%d7%99-%d7%94%d7%a9%d7%a0%d7%aa%d7%99-%d 7%94-60-%d7%9c%d7%9e%d7%93%d7%a2%d7%99-%d7%94%d7%aa%d7%a2%d7%95%d7%a4%d7%9 4-%d7%95%d7%94%d7%97/ SUMMARY:הכנס הישראלי השנתי ה-60 למדעי התעופה ו החלל (IACAS) DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location: מלון דן פ נורמה תל אביב + קמפוס הטכניון\, חיפה\n Zoom: \n Abstract: \n Details: \n הכנס הישראלי השנתי ה-60 למד עי התעופה והחלל (IACAS) יתקיים ביום רביעי\, 4. 3.20\, במלון דן פנורמה תל אביב\, וביום חמישי\ , 5.3.20\, בקמפוס הטכניון בחיפה.\n\nכנס זה\, שהי נו האירוע המרכזי בחיי הקהילה האווירונאו טית במדינת ישראל\, יחגוג השנה את שנתו ה-60 ! משתתפים בו כ-600 מהנדסים\, מדענים ומומחים בתחומי האוירונוטיקה והאסטרונאוטיקה מהא רץ והעולם.\n\nבזכות ערכו המדעי והטכנולוגי הרב\, הכנס הוא מפגש חי ותוסס ומעניין גם מב חינה חברתית ועסקית. בארגונו שותפים הגופי ם העיקריים העוסקים באוירונוטיקה וחלל במ דינה: משרד הביטחון וצה"ל\, התעשיות הביטחו ניות – התעשייה האווירית לישראל\, רפאל\, ת עש מערכות\, אלביט מערכות\, סוכנות החלל היש ראלית וכמובן האקדמיה – הטכניון\, אוניבר סיטת תל-אביב ואוניברסיטת בן-גוריון. לפיכ ך\, משתתפים בו דרך קבע נציגים של חברות אוי רונוטיות גדולות וקטנות העוסקות בפיתוח ו ייצור בתחום.\n\nתכנית הכנס תכלול הרצאות שמ חבריהן מגיעים ממדינות שונות ברחבי העולם\ , ביניהן הרצאות מוזמנות\, מהארץ ומחו"ל\, ות חרות ייחודית של פרויקטי סטודנטים. CATEGORIES:אירועים LOCATION: מלון דן פנורמה תל אביב + קמפוס הטכני ון\, חיפה END:VEVENT BEGIN:VEVENT UID:0-304@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200308T133000 DTEND;TZID=Asia/Jerusalem:20200308T143000 DTSTAMP:20230527T131446Z URL:https://aerospace.technion.ac.il/events/the-meir-hanin-international-a erospace-prize-guest-seminar-the-challenges-of-nonlinear-kalman-filtering/ SUMMARY:The Meir Hanin International Aerospace Prize Guest Seminar - The Ch allenges of Nonlinear Kalman Filtering DESCRIPTION:Lecturer:Prof. Mark L. Psiaki\n Faculty:Kevin T. Crofton Facult y Chair of Aerospace & Ocean Engineering\n Institute:Virginia Tech\, Black sburg\, VA\, U.S.A.\n Location:Auditorium 235\, Second Floor\, Aerospace E ng.\n Zoom: \n Abstract: \n Details: \n The challenges of nonlinear Kalman filtering are presented\, and a number of proposed solutions are examined . A Kalman filter forms an a posteriori estimate of the state of a dynamic system\, and it computes an estimation error covariance.  It provides th e optimal solution to any problem that is linear and Gaussian.  Various a pproximate Kalman filters and related estimation algorithms have been deve loped for nonlinear problems.  Some of them work well for important appli cations\, but none of them can provide a good solution to every conceivabl e nonlinear problem.  A given filter may diverge on certain problems.  A lternatively\, it may converge\, but yield much more estimation error than would an optimal filter.  Another filter may converge and achieve good a ccuracy\, but at a prohibitive cost in terms of computational resources.  The set of nonlinear filters that are reviewed and compared include the E xtended Kalman Filter (EKF)\, the Sigma-Points Filter -- also known as the Unscented Kalman Filter (UKF)\, the Particle Filter (PF)\, the Backward-S moothing Extended Kalman Filter (BSEKF) – a modification of the Moving H orizon Estimator (MHE)\, and the Gaussian Mixture Filter (GMF).  Nonlinea r problems that are used to examine these filters’ performance include s pacecraft attitude/rate/ moment-of-inertia estimation\, angles-only spacec raft orbit determination\, and the Blind Tricyclist nonlinear estimation b enchmark problem.  The filters are compared in terms of convergence relia bility\, accuracy\, and computational cost.  These comparisons demonstrat e that no single nonlinear filtering algorithm is superior to all others i n every respect.  Therefore\, a good estimation practitioner must know ab out many or most of these filtering options and choose among them to devel op the best solution to a given problem. CATEGORIES:Seminars LOCATION:Auditorium 235\, Second Floor\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-42@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200527T200000 DTEND;TZID=Asia/Jerusalem:20200527T210000 DTSTAMP:20221030T083447Z URL:https://aerospace.technion.ac.il/events/technion-rambam-alliance-fight ing-covid-19-together-webinar/ SUMMARY:Technion-Rambam Alliance | Fighting COVID-19 Together | Webinar DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Zoom Webinar\n Zoom: \n Abstract: \n Details: \nTechnion-Rambam Alliance | Fighting COVI D-19 Together\n\n\n******************************************************* ***********\nWhat happens when scientists\, engineers and physicians meet? \n******************************************************************\nZoom Webinar - May 27\, 2020 08:00 PM in Jerusalem\n************\nREGISTER\n* ***********\nModerators:\nProf. Rafael Beyar\, Rambam HCC\nProf. Alon Wolf \, Technion IIT\n*******************************************************\n Prof. Uri Sivan\nPresident\, Technion - Israel Institute of TechnologyDr. Michael Halberthal\nGeneral Director\, Rambam Health Care Campus---------- -------------------------\n► Rapid Test for COVID-19 ◄\n-------------- ---------------------\nProf. Naama Geva-Zatorsky\nRappaport Faculty of Med icine\, Technion\n\nProf. Mical Paul\nDirector Infectious Diseases Institu te\, Rambam Health Care Campus\n\n-----------------------------------\n► Pooling Method for Mass Detection of COVID-19 ◄\n---------------------- -------------\nProf. Roy Kishony\nFaculty of Biology\, Technion\n\nDr. Mor an Szwarcwort-Cohen\nDirector\, Virology Lab\, Rambam Health Care Campus\n \n-----------------------------------\n► COROBOT Care for Hospitals ◄\ n-----------------------------------\nProf. Gil Yudilevitch\nFaculty of Ae rospace Engineering\, Technion\n\nDr. Netanel Horowitz\nDirector\, Lymphom a Service and Hematology Clinical Trials\, Rambam Health Care Campus\n\n\n \n CATEGORIES:Events LOCATION:Zoom Webinar END:VEVENT BEGIN:VEVENT UID:0-64@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200527T200000 DTEND;TZID=Asia/Jerusalem:20200527T200000 DTSTAMP:20221031T080259Z URL:https://aerospace.technion.ac.il/he/events/%d7%95%d7%95%d7%91%d7%99%d7 %a0%d7%a8-%d7%a9%d7%99%d7%aa%d7%95%d7%a3-%d7%a4%d7%a2%d7%95%d7%9c%d7%94-%d 7%98%d7%9b%d7%a0%d7%99%d7%95%d7%9f-%d7%a8%d7%9e%d7%91%d7%9d-%d7%a0%d7%90%d 7%91%d7%a7%d7%99/ SUMMARY:וובינר | שיתוף פעולה טכניון-רמב"ם | נא בקים יחד בנגיף הקורונה DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:וובינר בז ום\n Zoom: https://technion.zoom.us/webinar/register/8915900606741/WN_kq op5IibRhaT96t62PRIbA\n Abstract: \n Details: \n Technion-Rambam Alliance | Fighting COVID-19 Together\n********************************************* *********************\nWhat happens when scientists\, engineers and physic ians meet?\n************************************************************** ****\nZoom Webinar – May 27\, 2020 08:00 PM in Jerusalem\nModerators:\nP rof. Rafael Beyar\, Rambam HCC\nProf. Alon Wolf\, Technion IIT\n********** *********************************************\nProf. Uri Sivan\nPresident\ , Technion – Israel Institute of TechnologyDr. Michael Halberthal\nGener al Director\, Rambam Health Care Campus\n——————————— –\n► Rapid Test for COVID-19 ◄\n———————————– \nProf. Naama Geva-Zatorsky\nRappaport Faculty of Medicine\, Technion\n\nP rof. Mical Paul\nDirector Infectious Diseases Institute\, Rambam Health Ca re Campus\n\n———————————–\n► Pooling Method for Mass Detection of COVID-19 ◄\n———————————–\nProf . Roy Kishony\nFaculty of Biology\, Technion\n\nDr. Moran Szwarcwort-Cohen \nDirector\, Virology Lab\, Rambam Health Care Campus\n\n————— ——————–\n► COROBOT Care for Hospitals ◄\n————— ——————–\nProf. Gil Yudilevitch\nFaculty of Aerospace Enginee ring\, Technion\n\nDr. Netanel Horowitz\nDirector\, Lymphoma Service and H ematology Clinical Trials\, Rambam Health Care Campus CATEGORIES:אירועים LOCATION:וובינר בזום END:VEVENT BEGIN:VEVENT UID:0-294@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200608T123000 DTEND;TZID=Asia/Jerusalem:20200608T133000 DTSTAMP:20230527T131059Z URL:https://aerospace.technion.ac.il/events/experience-based-prediction-of -unknown-environments-for-enhanced-belief-space-planning/ SUMMARY:Experience-Based Prediction of Unknown Environments for Enhanced Be lief Space Planning DESCRIPTION:Lecturer:Omri Asraf\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Zoom meeting - https://technion.zoom.us/j/91759816988\n Zoom: \n Abstract: \n Details: \n Autonomous navigation missions require online decision making abilities\, in order to choose from a given set of candidate actions an ac tion that will lead to the best outcome. In a partially observable setting \, decision making under uncertainty\, also known as belief space planning (BSP)\, involves reasoning about belief evolution considering realization s of future observations. Yet\, when  candidate actions lead the robot to an unknown environment the decision making mission becomes a very challen ging problem since without a map it is hard to foresee future observations .\nIn this thesis we develop a data-driven approach for predicting a distr ibution over an unexplored map\, generating future observations\, and comb ining these observations within BSP. We examine our approach and compare i t to existing BSP methods in a Gazebo simulation\, and demonstrate it ofte n yields improved performance. CATEGORIES:Seminars LOCATION:Zoom meeting - https://technion.zoom.us/j/91759816988 END:VEVENT BEGIN:VEVENT UID:0-63@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200610T163000 DTEND;TZID=Asia/Jerusalem:20200610T163000 DTSTAMP:20221031T075422Z URL:https://aerospace.technion.ac.il/he/events/%d7%9e%d7%a4%d7%92%d7%a9-%d 7%9e%d7%aa%d7%a2%d7%a0%d7%99%d7%99%d7%a0%d7%99%d7%9d-%d7%9e%d7%a7%d7%95%d7 %95%d7%9f-%d7%91%d7%a0%d7%95%d7%a9%d7%90-%d7%aa%d7%90%d7%a8%d7%99%d7%9d-%d 7%9e%d7%aa%d7%a7%d7%93/ SUMMARY:מפגש מתעניינים מקוון בנושא תארים מתק דמים - 10.6.20 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: https://t echnion.zoom.us/j/93994643424\n Abstract: \n Details: \n ביום רביע י 10.6.2020 בשעה 16:30 נקיים מפגש מקוון בנושא תא רים מתקדמים.\nקישור לעמוד האירוע\n\nבמפגש נספר על הלימודים לתארים מתקדמים בפקולטה ונשיב לשאלותיכם*.\nבין המשתתפים\, דיקן הפק ולטה\, סגן הדיקן לתארים מתקדמים\, רכזת תאר ים מתקדמים ונציג המשתלמים.\n\nנשמח לראותכ ם.\n\nיש לכם כבר שאלות? תוכלו לשלוח אותן מר אש אל grad@technion.ac.il CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-303@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200805T163000 DTEND;TZID=Asia/Jerusalem:20200805T173000 DTSTAMP:20230527T131411Z URL:https://aerospace.technion.ac.il/events/effect-of-thermal-boundary-con ditions-on-heat-and-mass-transfer-processes-in-rarefied-gas-flows/ SUMMARY:Effect of thermal boundary conditions on heat and mass transfer pro cesses in rarefied gas flows DESCRIPTION:Lecturer:Yaron Ben Ami\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:h ttps://technion.zoom.us/j/94450620797\n Zoom: \n Abstract: \n Details: \n Studies on rarefied gases consider gas flows where the characteristic leng th or time scale is of the order of the molecular mean-free path or time\, respectively. Under such conditions\, the gas cannot be treated as contin uum\, and the molecular properties of the medium must be taken into accoun t. These scenarios prevail in small-scale mechanical systems applications as well as at low-pressure conditions. In marked difference from incompres sible flow fields\, the coupling between the dynamic and thermodynamic des criptions of rarefied gas flows is prevalent\, and may be induced through externally-imposed thermal excitation of a surface. The goal of the presen t research is to explore the effect of thermal conditions at a solid bound ary on heat and mass transfer phenomena in rarefied gases.\nThe seminar wi ll cover two of the topics studied in my work: (i) the impact of thermal c onditions on the acoustic field of a pulsating body at short length and ti me scales\; (ii) nonlinear thermal effects in unsteady shear flows of rare fied gases. In each setup\, the analysis combines numerical simulations (b ased on the direct simulation Monte Carlo method) with limit-case analytic al investigations\, in an effort to shed light on the coupling between the rmal and dynamic phenomena at far-from-equilibrium conditions. CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/94450620797 END:VEVENT BEGIN:VEVENT UID:0-292@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200812T163000 DTEND;TZID=Asia/Jerusalem:20200812T173000 DTSTAMP:20230525T085301Z URL:https://aerospace.technion.ac.il/events/investigation-of-methanol-comb ustion-in-an-opposed-jet-combustor/ SUMMARY:Investigation of Methanol Combustion in an Opposed Jet Combustor DESCRIPTION:Lecturer:Ariel Sharon\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:ht tps://technion.zoom.us/j/99852933549\n Zoom: \n Abstract: \n Details: \n T ransfer to sustainable energy is the requirement of the present hour &\ ; there has been a considerable push towards renewable non-combustion-base d energy generation. Nevertheless\, it is estimated that conventional comb ustion of hydrocarbons will still be the most significant energy source fo r the next decades. Considering this\, it is of paramount importance to op timize combustion-based energy generation. One possible area of minimizing the environmental impact is by switching to biofuels\, and one such promi sing biofuel is Methanol (CH3OH).\nTo advocate this transfer towards metha nol\, fundamental knowledge of its emission characteristics is required\, especially trace pollutants like Formaldehyde (CH2O). In combustion engine ering\, Chemical Kinetics Models are a useful tool to predict these combus tion behaviors. These models are only validated against a limited set of e xperimental measurements. Considering this\, it is important to validate t he existing chemical mechanisms for a broader set of operational range.\nT his research provides for detailed validation of the existing Methanol che mical kinetic mechanism by correlating simulation &\; experimental data from Methanol oxidation in an Opposed Jet Combustor (OJC). The work inclu des experimental Chemiluminescence &\; temperature measurement for both atomized &\; vaporized Methanol combustion\, which are then correlated against Chemkin OPPDIF simulations.\nAdditionally\, the presentation will showcase simulation results focused on identifying methods of minimizing Formaldehyde (CH2O) emission. These parametric simulations explores the no vel method of controlling CH2O emission by using Water mixed Methanol.\nZo om Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/99852933549 END:VEVENT BEGIN:VEVENT UID:0-286@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200909T163000 DTEND;TZID=Asia/Jerusalem:20200909T173000 DTSTAMP:20230525T071004Z URL:https://aerospace.technion.ac.il/events/fuel-efficient-cross-track-dis tance-establishment-in-satellite-formations/ SUMMARY:Fuel-Efficient Cross-Track Distance Establishment in Satellite Form ations DESCRIPTION:Lecturer:Yonatan Amit-Shapira\n Faculty:Department of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Loc ation:https://technion.zoom.us/j/91675095158\n Zoom: \n Abstract: \n Detai ls: \n Satellite formations have numerous applications. However\, the init ial establishment of such formations can require a high fuel expenditure\, due to cross-track distance requirements. This work proposes a strategy t o significantly reduce the fuel required for the formation establishment. Instead of direct out-of-plane maneuvers\, it is suggested to use in-plane maneuvers\, while utilizing natural forces\, specifically the J2 perturba tion. This methodology extends the establishment duration\, and thus requi res re-establishment of the along-track distance. Analytical expressions f or the cross-track distance and the establishment duration are derived for the case of impulsive thrust\, with and without drag. For many cases\, th e expected duration is reasonable\, and the fuel saving is shown to be con siderable.\nFor the continuous thrust case\, optimal control methods were used. The proposed strategy is proven to be optimal for an example problem with two cases: limited and unlimited thrust magnitude. Finally\, the cas es of impulsive and continuous thrust are compared.\nZoom Meeting\n\n  \; CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91675095158 END:VEVENT BEGIN:VEVENT UID:0-284@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200914T123000 DTEND;TZID=Asia/Jerusalem:20200914T133000 DTSTAMP:20230525T070917Z URL:https://aerospace.technion.ac.il/events/integration-of-aeroelastic-eff ects-in-flight-6dof-simulations/ SUMMARY:Integration of aeroelastic effects in flight (6dof) simulations DESCRIPTION:Lecturer:Ioffe Olga\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:http s://technion.zoom.us/j/91932575862\n Zoom: \n Abstract: \n Details: \n Six -degrees-of-freedom (6DOF) simulations to outline the flight path of missi les and predict their rigid body behavior\, are normally conducted in the time domain using flight-mechanic equations of motion with nonlinear quasi -steady aerodynamic coefficients\, gravity effects and a realistic control system. Dynamic aeroelastic simulations are normally performed for stabil ity and loads analysis at a single height-velocity combination\, using lin ear frequency-domain equations of motion where the structure is represente d in modal coordinates and the unsteady aerodynamic coefficient matrices a re a function of frequency. Aeroelastic effects are sometimes introduced i n 6DOF simulations thru static aeroelastic corrections or introduction of modal frequencies. A 6DOF simulation with integrated dynamic aeroelastic e ffects would seamlessly predict elastic vibrations and aero-servo-elastic interactions with change of flight conditions. It will enable study of par ameter variations and Monte Carlo analysis.\n\nTo be used in in state-spac e time-domain formulation\, the unsteady aerodynamics\, commonly represent ed in linear analyses by frequency domain complex functions\, are approxim ated via Rational Function Approximation (RFA). A methodology for the impl ementation of quasi-steady aerodynamic coefficients from Wind Tunnel or CF D calculation in the RFA matrices\, for matching the quasi-steady rigid bo dy dynamics\, is presented. RFA is canonically calculated for each flight condition independently. This work introduces a revised RFA procedure that leads to state definitions that are consistent across changing flight con ditions and yield continuous state-space equations over the entire flight envelope. Then\, a simplified Simulink™ simulation is set to access a pr e-calculated unsteady aerodynamic database\, retrieve time-dependent state -space matrices and demonstrate an integrated simulation run. CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91932575862 END:VEVENT BEGIN:VEVENT UID:0-289@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200916T163000 DTEND;TZID=Asia/Jerusalem:20200916T173000 DTSTAMP:20230525T071508Z URL:https://aerospace.technion.ac.il/events/assessment-of-load-bearing-cap abilities-of-cfrp-filament-wound-structures/ SUMMARY:Assessment of Load Bearing Capabilities of CFRP Filament Wound Stru ctures DESCRIPTION:Lecturer:Yaniv Seri\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:http s://technion.zoom.us/j/95290027997\n Zoom: \n Abstract: \n Details: \n Cor rect estimation of load bearing capabilities and prediction of failure has an important role in design and quality control of filament wound (FW) co mposite fiber reinforced plastic (CFRP) structures such as composite overl apped pressure vessels\, filament wound pipes and other. Such structures a re widely used in aerospace\, military and gas industries and must provide safe operation.\n\nThere is a limited number of studies and methods that are used today for assessment of load bearing capabilities of FW CFRP stru ctures. The present research is intended to review the state-of-the-art pr actices and assist in development of a new approach for evaluation of stru ctural integrity of filament wound structures at loads below those normall y applied during proof testing and improve operational safety of CFRP pres sure equipment.\n\nDuring the present research \, we have tested and analy zed NOL ring\, a parallel filament wound hoop test specimens\, for identif ication of characteristic stages of damage accumulation and development us ing experimentally measured characteristics of acoustic emission (AE)\, st rain and displacement. A correlation between fracture loads and different parameters of AE was observed. It was shown also that acoustic emission te chnology can detect effectively matrix micro-cracking\, fiber brakeage and other damage mechanisms related to CFRP damage. The results of the tests of NOL rings and full-scale products test showed similarity in fracture pr operties including stages of damage accumulation and developing that were confirmed experimentally by acoustic emission and strain measurements. CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/95290027997 END:VEVENT BEGIN:VEVENT UID:0-282@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20200930T163000 DTEND;TZID=Asia/Jerusalem:20200930T173000 DTSTAMP:20230525T070835Z URL:https://aerospace.technion.ac.il/events/a-diesel-engine-with-a-catalyt ic-piston-surface-to-propel-small-aircraft-at-high-altitudes-a-theoretical -study/ SUMMARY:A Diesel Engine with a Catalytic Piston Surface to Propel Small Air craft at High Altitudes – A Theoretical Study DESCRIPTION:Lecturer:Kadmiel Karsenty\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:https://technion.zoom.us/j/94169102438\n Zoom: \n Abstract: \n Details: \n There has recently been a large increase in development activities of r emotely-controlled and autonomous miniature aerial vehicles (MAV). Militar y\, scientific\, law enforcement and mapping usage are among the important potential applications that motivate this effort. Another promising area is remote observation of hazardous environments which are hard or inaccess ible to ground vehicles. Among the more severe limiting factors of the MAV development are the engine thermal efficiency and its performance degrada tion at high altitudes.\nIn this work we propose a unique method to extend the upper-limit altitude with no noticeable extra weight. We propose a sp ecial in-cylinder steam reforming approach to significantly increase the e ngine efficiency at high altitudes\, thus allowing engine operation at hig her altitudes with a negligible weight penalty. The gain in the engine per formance at high altitude is attributed to the present unique method of in ternal heat recovery (in-cylinder steam reforming) by which a wider flamma bility and higher burning velocity are achievable. In the present research we analyze the effect of the in-cylinder steam reforming process on the e ngine performance at high altitude. The results of the research show that by the employment of the internal steam reforming concept in internal comb ustion engines (in either 2- or 4-stroke engines)\, it is possible to incr ease the indicated efficiency and engine brake power and therefore decreas e the fuel consumption. Moreover\, due to the higher in-cylinder pressure without an increase in the temperature\, the cycle effectiveness is higher while keeping the same amount of NOx emission.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/94169102438 END:VEVENT BEGIN:VEVENT UID:0-290@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201012T123000 DTEND;TZID=Asia/Jerusalem:20201012T133000 DTSTAMP:20230525T071533Z URL:https://aerospace.technion.ac.il/events/constellation-design-for-regio nal-space-borne-geolocation/ SUMMARY:Constellation Design for Regional Space-borne Geolocation DESCRIPTION:Lecturer:Nadav Mailhot\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:h ttps://technion.zoom.us/j/92632914745\n Zoom: \n Abstract: \n Details: \n Time difference of arrival geolocation allows for the position estimation of a terrestrial emitter by measuring its signals with 3 or more receivers . This type of geolocation\, also known as hyperbolic fix\, is used by a v ariety of satellite and aircraft systems worldwide. Existing systems do no t provide continuous coverage of a target area\, instead relying on infreq uent passes of satellites or keeping aircraft in flight for extended perio ds of time.\nIn this study we design constellations of satellites which ca n provide continuous geolocation services in a specific target region. The constellations are designed using global optimization techniques of exhau stive search and genetic algorithms with the aim of minimizing the lower b ound of the geolocation estimation error\, which is a variant of the Cram ér-Rao lower bound. Additionally\, the estimation itself is carried out w ith a specialized algorithm\, the constrained extended Kalman filter.\nThe design methodology and the efficacy of the estimation algorithm are demon strated with Monte Carlo simulations of geolocation with one of the result ing constellations. The constellation is shown to provide consistent cover age with a low estimation error\, and the estimator is shown to be efficie nt.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/92632914745 END:VEVENT BEGIN:VEVENT UID:0-281@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201014T163000 DTEND;TZID=Asia/Jerusalem:20201014T173000 DTSTAMP:20230525T070815Z URL:https://aerospace.technion.ac.il/events/large-eddy-simulation-of-rotor s-filtered-actuator-line-modelling-of-wind-turbines-and-aeroacoustics-of-p ropeller/ SUMMARY:Large Eddy Simulation of Rotors: Filtered Actuator Line Modelling o f Wind Turbines and Aeroacoustics of Propeller DESCRIPTION:Lecturer:Ronith Stanly\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:h ttps://technion.zoom.us/j/95290857526\n Zoom: \n Abstract: \n Details: \n Engineering devices employing rotors such as propellers on UAV’s\, wind and tidal turbines play a vital role in both propulsion and energy extract ion.  These devices feature complex unsteady turbulent flowfields and hav e significant non-local effects related to downstream wake interactions an d far-field noise.  In the past decade\, the use of advanced turbulence m odeling approach within a computational fluid dynamics (CFD) approach\, su ch as large eddy simulations (LES) have become more popular.  LES offers higher fidelity but also increases computational cost.  When dealing with multi-rotor devices such as quad-copters or wind farms the cost of blade- resolved LES becomes prohibitive.  Combining LES with the family of lower -fidelity models\, called actuator line models (ALM)\, has grown in popula rity in the past decade.  ALM models replace full blade resolution with a n array of actuator points or lines parameterized by aerodynamic lift/drag polar plots along the blades.  Body forces computed based on these actua tor points are then projected onto the LES flow mesh mimicking the effect of rotating blades on the flow.  In this seminar\, an ALM model is implem ented into an in-house high-fidelity LES code\, called MIRACLES\, and appl ied to (a) rotor wake flow and noise predictions\, and (b) several benchma rk single- and twin-wind turbine cases.  Wherever possible comparisons ar e made to both measured data and previous simulation results to assess the performance of the combined LES/ALM approach for simulating rotor flows.   Novel aspects of this study include the implementation of the Ffowcs-Wi lliams Hawkings (FWH) noise model and the recent Filtered-ALM and its MPI parallelization.  Simulations typically are run on several hundred CPU co res and take several days to a week to gather flow and statistical results . CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/95290857526 END:VEVENT BEGIN:VEVENT UID:0-288@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201028T163000 DTEND;TZID=Asia/Jerusalem:20201028T173000 DTSTAMP:20230525T071335Z URL:https://aerospace.technion.ac.il/events/evolution-of-chaos-in-long-ter m-propagation-of-high-earth-orbits/ SUMMARY:Evolution of Chaos in Long-term Propagation of High Earth Orbits DESCRIPTION:Lecturer:Paolo Izzo\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology and University of Rome 'La Sapienza'\n Location:https://technion.zoom.us/j/99048462414\n Zoom: \n Abstract: \n Details: \n The numerical detection of resonances us ing dynamical indicators is an efficient tool for eval- uating the long-te rm stability and for discriminating between order and chaos. In this regar d\, methods based on the analysis of vectors deviating from an initial ref erence orbit\, stemming from the pioneering work of Lyapunov\, have been w idely employed in the past decades. Especially High Earth Orbits (HEO)\, g overned by the interplay of multiple perturbations accumulated over long t ime spans\, show an orbital evolution that can result in a strong sensitiv ity to the initial condi- tions. Using an orbital model defined in terms o f Milankovitch vectorial elements\, stability maps are developed to target natural disposal trajectories in the osculating space. However\, these ma ps have to be initialized to account the short-periodic terms that may hav e relevant effects on the re-entry solutions. Using the direct approach of Kozai\, we derive the analytical short-period cor- rection for J2 and des ign a numerical algorithm based on the Fast Fourier Transform for validati on purposes. Indeed\, for HEO orbits\, the lunisolar effect becomes releva nt and the short-period correc- tions must be included for an accurate sat ellite dynamics. Therefore\, we extend both the analytical and numerical d evelopments to include the lunisolar perturbations as well\, and to obtain a first- order\, singularity-free\, full-perturbative transformation. The proposed methodology has important applications for satellite lifetime pr ediction and for passive space debris removal.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/99048462414 END:VEVENT BEGIN:VEVENT UID:0-287@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201109T123000 DTEND;TZID=Asia/Jerusalem:20201109T133000 DTSTAMP:20230525T071035Z URL:https://aerospace.technion.ac.il/events/detailed-design-optimization-o f-a-solid-rocket-motor/ SUMMARY:Detailed Design Optimization of a Solid Rocket Motor DESCRIPTION:Lecturer:Ohad Ben Horin\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: https://technion.zoom.us/j/97716921243\n Zoom: \n Abstract: \n Details: \n Solid-propellant rocket propulsion is commonly used for both military and civilian launch systems. In solid rocket motors the required thrust profi le is determined by its design and cannot be changed or controlled after p roduction. In addition to the thrust profile\, there are other design goal s and constraints\, both at a system level and at the rocket motor level. This makes the design of a rocket a complex process that involves many cou pled design variables.. The detailed design is largely based on profession al experience applied in a manual\, iterative process\, and therefore not readily available to the system engineer. Instead\, the system engineer ne eds to rely on rough estimations for the propulsion system during initial system design. These estimations could be non-feasible regarding the rocke t motor or sub-optimal for the complete system.\nThe current research pres ents a novel model of a solid rocket motor that combines several models wi th different levels of accuracy in order to quickly estimate  the impact of the design variables on the systems' performance. The model is employed for quick\, automated initial design and is used in finding an optimal so lution of several case studies. Furthermore\, a comparative study of selec ted optimization algorithms is presented in order find the best suitable a lgorithm and parameters for a robust\, prompt convergence.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/97716921243 END:VEVENT BEGIN:VEVENT UID:0-280@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201118T163000 DTEND;TZID=Asia/Jerusalem:20201118T173000 DTSTAMP:20230525T070751Z URL:https://aerospace.technion.ac.il/events/graph-based-model-reduction-me thods-for-multi-agent-systems/ SUMMARY:Graph-Based Model Reduction Methods for Multi-Agent Systems DESCRIPTION:Lecturer:Noam Leiter\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:htt ps://technion.zoom.us/j/96771910881\n Zoom: \n Abstract: \n Details: \n Mo del-order reduction is an essential tool for large-scale systems introduce d by modern Technologies for which full order simulation and controller de sign and implementation may be numerically and computationally infeasible. Model order reduction is a well established field of research in control and systems theory. Of particular interest in recent years is the study of model reduction for multi-agent systems which are characterized by their increasingly large scales.\nMulti-agent systems have an underlying network structure represented by graphs. For large-scale graphs\, combinatorial o perations can be performed to obtain reduced graph sizes. In general\, the re is an interest to understand how certain graph reduction operations pre serve spectral and combinatorial properties of the graph. We explore in th is talk certain graph reductions that satisfy an interlacing property betw een spectral properties of graphs represented by matrices. We show how two types of graph contractions\, cycle invariant contractions and node-remov al equivalent contractions\, lead to spectral interlacing of the normalize d-Laplacian and Laplacian graph matrices\, and we provide efficient algori thms for performing these contractions.\nWe then leverage these results on graph reductions to study model reduction of large-scale networked dynami c systems.  We show how graph contractions can be used to obtain reduced- order models with guarantees on the performance of the reduced model compa red to the original model.  In this direction\, we derive an a priori H2 error reduction bound for graph-based interlacing reduced models. We then demonstrate these results on the classical controlled consensus model.\nZo om Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/96771910881 END:VEVENT BEGIN:VEVENT UID:0-285@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201123T123000 DTEND;TZID=Asia/Jerusalem:20201123T133000 DTSTAMP:20230525T070942Z URL:https://aerospace.technion.ac.il/events/moving-target-interception-wit h-a-quadrotor-using-classical-guidance/ SUMMARY:Moving Target Interception with a Quadrotor using Classical Guidanc e DESCRIPTION:Lecturer:Aron Hadad\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:http s://technion.zoom.us/j/96731911958\n Zoom: \n Abstract: \n Details: \n In this work we test the concept of intercepting a moving target with a quadr otor while using  classical guidance laws originally developed in the fi eld of missile guidance.\nFirst\, the dominant factors at play in an engag ement between a quadrotor interceptor and a constant-speed non-maneuverin g adversary\, with similar speed capabilities\, are analyzed. Thrust-to-w eight requirements are derived in the processes of finding bounds on the ability of a quadrotor to maintain constant speed or acceleration\, featur es which are sometimes desirable when solving a guidance problem. Next\, several guidance laws are adapted from two well-known guidance principals with the purpose of addressing some of the key characteristics of the en gagement and interceptor platform in question.\nThe key characteristics ar e low-speed/low-range engagements\, thrust of the same order of magnitude as gravity and thrust dynamics which are quicker than angular dynamics o f the quadrotor body. Next\, the guidance laws are calibrated and tested i n a simulated environment and scenarios are gradually scaled down to the size of our lab exposing geometric constraints which are critical when de signing lab testing procedures. Finally\,\na sub-set of the guidance laws are exhaustively tested in the lab. The results both validate the simulat ion and provide insight into critical real-world issues related to guidan ce with a quadrotor.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/96731911958 END:VEVENT BEGIN:VEVENT UID:0-283@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201125T163000 DTEND;TZID=Asia/Jerusalem:20201125T173000 DTSTAMP:20230525T070853Z URL:https://aerospace.technion.ac.il/events/agglomeration-in-composite-pro pellants-containing-different-nano-aluminum-powders/ SUMMARY:Agglomeration in Composite Propellants containing Different Nano-Al uminum Powders DESCRIPTION:Lecturer:Ortal Cohen\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:htt ps://technion.zoom.us/j/91226230537\n Zoom: \n Abstract: \n Details: \n Mi cron-sized aluminum powder is added to solid propellants in order to incre ase their performance and to suppress combustion instabilities. During the combustion\, aluminum particles accumulate and form agglomerates. Agglome ration may cause loss of potential chemical energy due to incomplete combu stion\, two-phase flow losses\, and accumulation of slag in the motor. A w ell-known method to reduce agglomeration is the use of nano-aluminum powde rs (such as ALEX). The specific surface of nano-powders is larger than tha t of micron‑sized powders\, therefore their reaction and heating rates a re higher. The nano-aluminum particle ignites faster with shorter burning time\, resulting in a higher burning rate.\nIn order to further improve th e performance\, different materials were investigated for coating nano-alu minum particles. Two of the powders considered are V-ALEX\, a fluoropolyme r (Viton) coated nano-aluminum\; and L-ALEX\, stearic acid coated nano-alu minum. A thin layer of coating may promote particle ignition\, which decre ases the agglomerate size and\, thus\, reduces the two-phase flow losses.\ nThe purpose of the research is to examine the effect of ALEX\, V-ALEX and L‑ALEX powders on the agglomeration phenomenon in solid AP/HTPB propell ants\, at different operating pressures. The agglomeration phenomenon was measured by high speed video photography in order to record the combustion process of propellant strands. The strands were burned inside a windowed pressure chamber\, allowing measurements of the agglomerates size and numb er. The experimental data show that coated nano-powders exhibit reduced ag glomeration\, in terms of number of agglomerates and their volume\, and th at propellants containing V-ALEX powder experienced the largest decrease i n agglomeration.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91226230537 END:VEVENT BEGIN:VEVENT UID:0-291@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201130T163000 DTEND;TZID=Asia/Jerusalem:20201130T173000 DTSTAMP:20230525T085234Z URL:https://aerospace.technion.ac.il/events/aero-thermal-elastic-modelling -of-plates-in-hypersonic-flow/ SUMMARY:Aero-thermal-elastic modelling of plates in hypersonic flow DESCRIPTION:Lecturer:Maxim Freydin\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:h ttps://technion.zoom.us/j/91489432408\n Zoom: \n Abstract: \n Details: \n Fluid-structure interaction in hypersonic flow has seen an increased inter est among researchers in response to the worldwide race to sustainable hyp ersonic flight. The interaction between inertial\, elastic\, aerodynamic\, and thermal loads in high Mach flows is an extension of classical aeroela sticity. To investigate the fundamental physics that govern the aero-therm al-elastic interaction\, elastic plates are utilized in super/hypersonic w ind tunnel experiments for their relative simplicity of installation\, man ufacture\, and analysis. Numerous recent experiments investigated the resp onse of elastic plates using advanced measurement techniques (for pressure \, temperature\, and deformation) focusing on shock-wave/boundary-layer an d structure interaction\, flutter onset and limit-cycle oscillation\, and impinging shock effects\, with more planned for the upcoming years. Many o f those experimental studies are published with little\, and in some cases no\, computational or theoretical fluid-structure analysis. This demonstr ates the need for accurate and accessible theoretical models for the analy sis of plates in hypersonic flow with the different physical effects inclu ded. In the present work\, theoretical-computational models of plates in h ypersonic flow are derived and formulated to be used in linear and nonline ar analysis of static and dynamic problems. An overview of the derivation of a plate-cavity-freestream model is presented. A novel structural model is derived that includes the effect of elastic in-plane edge constraints\, which is shown to be important to the nonlinear static and dynamic plate response. Analysis of recent experiments conducted by researchers from the US Air Force Research Laboratory and the University of Maryland is presen ted with correlation between theory and experiment.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91489432408 END:VEVENT BEGIN:VEVENT UID:0-269@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201202T163000 DTEND;TZID=Asia/Jerusalem:20201202T173000 DTSTAMP:20230525T064303Z URL:https://aerospace.technion.ac.il/events/towards-laser-communication-be tween-cubesats-and-drones/ SUMMARY:Towards Laser Communication Between Cubesats and Drones DESCRIPTION:Lecturer:Leonid Pogorelyuk\n Faculty:Department of Aeronautics and Astronautics\,\n Institute:MIT\n Location:https://technion.zoom.us/j/9 2064872509\n Zoom: \n Abstract: \n Details: \n In the upcoming decade\, gr ound-to-space laser links will become abundant in scientific and industria l applications and Unmanned Aerial Vehicles (UAV) will transfer increasing ly larger volumes of data. Major companies such as SpaceX and OneWeb will be deploying satellite constellations to provide high data-rate and low-la tency communication services\, including Free Space Optical (FSO) communic ation\; while smaller-scale cubesat missions are beginning to use lasers a s low-mass\, high-bandwidth and license-free alternatives to radio communi cation. FSO links can provide remote sensing UAV with higher data-rates\, search and rescue missions with better accessibility\, and security-relate d applications with more reliable connectivity. Combined with satellite co nstellations\, drones also have the potential to provide aerial high-speed internet coverage for remote areas.\nYet\, laser communication from Low E arth Orbit (LEO) to small-sized UAV requires several technology demonstrat ions. Classical optical methods for telescope calibration (using stars) ar e too slow for rapid attitude estimation\, while inertial sensors are not precise enough. A proposed approach to achieving the arcsecond-level preci sion necessary for signal tracking and acquisition\, is to deduce the orie ntation of the instrument by rapidly processing camera images to identify distant control points. Another challenge associated with airborne telesco pes is the turbulence-induced wavefront disturbance. To improve the qualit y of the signal and reduce transmitter power requirements\, wavefront sens ing techniques from large stationary observatories need be adapted to low- cost mobile telescopes. This seminar discusses the development and testing of algorithms for high-precision image-based attitude determination and w avefront sensing from vehicles.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/92064872509 END:VEVENT BEGIN:VEVENT UID:0-274@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201207T123000 DTEND;TZID=Asia/Jerusalem:20201207T133000 DTSTAMP:20230525T065216Z URL:https://aerospace.technion.ac.il/events/a-direct-numerical-simulation- on-aerofoil-noise-due-to-flow-separation-and-stall/ SUMMARY:A Direct Numerical Simulation on Aerofoil Noise due to Flow Separat ion and Stall DESCRIPTION:Lecturer:Associate Professor Jae-Wook Kim\n Faculty:Engineering and Physical Sciences\n Institute:University of Southampton\n Location:ht tps://technion.zoom.us/j/8996991299\n Zoom: \n Abstract: \n Details: \n Ae rofoil self-noise produced by flow separation and stall is relatively litt le understood regarding the underlying generation mechanisms. The focus of this talk is to provide an improved level of understanding particularly w ith regard to the dipole noise sources utilising a high-fidelity direct nu merical simulation. A NACA0012 aerofoil is considered under three differen t flow conditions at a Reynolds number of 50\,000 and a Mach number of 0.4 .  These include: a pre-stall condition with a laminar separation bubble\ , near-stall and fully stalled. The noise radiation in the far-field is si gnificantly increased at low frequencies for the full-stall case for all o bserver directions which is consistent with previous experimental observat ions. The dominant source regions for each configuration are identified fo r low\, medium and high frequencies\, separately. A number of key findings are made concerning the source characteristics in full-stall which differ considerably from the lower angle of attack cases. It is found that the l ocation of the dominant sources changes more significantly with frequency for the full-stall case. Additionally\, for medium to high frequencies the maximum acoustic source amplitude is weaker for the full-stall case\, des pite comparable levels observed in the far-field. This seemingly contradic tory observation highlights the importance of phase variations in the wall pressure fluctuations. For the frequencies considered in this work it is shown that the\nfull-stall case usually produces a relatively more in-phas e source distribution\, resulting in a more efficient radiation despite th e lower amplitude levels. The important flow structures which are responsi ble for the dipole sources are also identified through analysis of the pre ssure field at isolated frequencies. It is found that for low frequencies coherent structures in the shear layer are responsible for the scattering of the wall pressure fluctuations at the TE\, which agrees with previous f indings in the literature. However\, at medium and high frequencies the sh ear layer structures are found to be relatively weak in the proximity of t he TE. This indicates that the noise may be generated through other means\ , for example scattering of fluctuating pressure induced by vortices shed from the TE.\nJoin the Zoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/8996991299 END:VEVENT BEGIN:VEVENT UID:0-279@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201223T163000 DTEND;TZID=Asia/Jerusalem:20201223T173000 DTSTAMP:20230525T070725Z URL:https://aerospace.technion.ac.il/events/quantitative-correlation-betwe en-strains-measurement-and-damage-severity-in-a-structure-with-local-openi ng/ SUMMARY:Quantitative correlation between strains measurement and damage sev erity in a structure with local opening DESCRIPTION:Lecturer:Itay Farajun\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:ht tps://technion.zoom.us/j/8626539141\n Zoom: \n Abstract: \n Details: \n Wh ile SHM science and engineering have matured in recent decades\, by now in deed a coherent and well-established branch of structural mechanics\, most practicalities are of qualitative nature. The present work suggests a sim ple\, user friendly\, method for assessing both damage location and level of damage deterioration along service life.\nSetting is within framework o f plane stress isotropic elasticity\, focusing on a representative configu ration of a large plate that contains a hole type damage at a distance fro m the boundaries\, with a-priori unknown location. Health monitoring is ba sed on inducing a remote uniform tension field and measuring strains at se lected points. The underlying assumption is that\, according to Saint-Vena nt principle\, at sufficient distance from the hole the field characterist ics are reasonably approximated by the classical Kirsch solution.\nStartin g with the simple case of circular hole we show how just a few strain meas urements can expose the location of the hole\, its radius and possible det erioration (increasing hole diameter). Next\, using Inglis and finite elem ent solutions\, we turn to more complicated shapes\, like elliptic and squ are holes\, and show how the monitoring procedure provides damage location and size of the “equivalent circular hole”. That notion will be exami ned in some detail\, including sensitivities\, reliability\, and limits of validity. Field strains induced by remote tension have been taken from FE computational analysis or from available analytical solutions.\nWe shall argue that the predictive power of the suggested method\, even though of a pproximate nature\, provides a practical and simple tool of SHM. Possible extension to anisotropic composite material and other types of structural damage plates will be briefly discussed.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/8626539141 END:VEVENT BEGIN:VEVENT UID:0-268@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20201230T163000 DTEND;TZID=Asia/Jerusalem:20201230T173000 DTSTAMP:20230525T064227Z URL:https://aerospace.technion.ac.il/events/neighboring-extremal-path-appl ications-for-rocket-trajectory-shaping/ SUMMARY:Neighboring Extremal Path Applications for Rocket Trajectory Shapin g DESCRIPTION:Lecturer:Mor Rosenheim\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:h ttps://technion.zoom.us/j/98155466137?pwd=WHFrUXFvNDQzY0tkTkRUZmsrcVlEQT09 \n Zoom: \n Abstract: \n Details: \n A guided rocket system performance is often evaluated by solving an optimal control problem which minimizes a p re-defined objective function\, e.g. control effort\, while satisfying req uired boundary conditions. However\, rocket guidance has constrict “real -time” computational and duration restrictions\, which the optimum solut ion methods do not satisfy.  Therefore\, there is need to efficiently obt ain a solution close to the optimal solution without the accompanying comp utational burdens.\nThe current research presents a hybrid analytic and nu merical approach for solving a required dynamic physics problem\, while ta king advantage of pre-defined optimal solution data. The chosen method\, n amed Neighboring Extremal Path method\, proposes a linearization of the no nlinear complex dynamic equations and optimality conditions around an opti mal reference rocket trajectory\, creating a linear “Two Point Boundary Value Problem” (TPBVP). The TPBVP resulting augmented neighboring contro l shall drive the rocket along a required path to the desired impact point . Both open loop (OL) and closed loop (CL) Neighboring analyses were condu cted. The OL neighboring analysis was done with fixed final time and termi nal impact point perturbations\, using Indirect Shooting and Backwards Swe ep approaches of solution. The CL neighboring optimum feedback law was tes ted in the presence of parameter uncertainties\, using Backwards Sweep app roach for fixed and unspecified terminal time.\nThe analysis showed the Ne ighboring Extremal method validity with perturbed rocket conditions (inclu ding wind) while reviewing a wide range of parameter uncertainties. Mostly \, the analyses showed acceptable impact point errors\, however\, in order to fully fulfill the requirements\, an unspecified final time closed loop neighboring control is necessary.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/98155466137?pwd=WHFrUXFvNDQzY0tkTkRUZms rcVlEQT09 END:VEVENT BEGIN:VEVENT UID:0-271@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210106T163000 DTEND;TZID=Asia/Jerusalem:20210106T173000 DTSTAMP:20230525T064427Z URL:https://aerospace.technion.ac.il/events/finding-the-worst-case-behavio r-of-an-accelerating-rocket-due-to-side-wind-disturbances/ SUMMARY:Finding the Worst-Case Behavior of an Accelerating Rocket due to Si de-Wind Disturbances DESCRIPTION:Lecturer:Mor Friedler\n Faculty:Aerospace engineering\n Institu te:Technion – Israel Institute of Technology\n Location:https://technion .zoom.us/j/97200263778\n Zoom: \n Abstract: \n Details: \n Flight control law clearance provides the conditions needed for the system to operate in the stability boundaries. One way to do so is to test all the parameters a nd variables in question. This method is time and resources wasteful\, and not free of errors. A different approach\, that has already been proven e ffective\, is to use optimization tools. Instead of proving the system can endure every condition\, the search can be narrowed to find only the crit ical conditions and determine a boundary of safety.\nWhen it comes to rock ets\, there are various factors in the acceleration phase that affect its trajectory. A very important factor is side-winds that cause angles-of-sid eslip that affect the rocket's motion during the acceleration phase\, and eventually the whole trajectory by shifting the ballistic plane.\nThe chos en optimization method for solving this problem is Neustadt's. This is a simple method for finding the minimal effort required to bring a linear sy stem from the initial condition to its ending condition with minimum contr ol effort. This mathematical method was chosen since it yields a simple an alytical solution as compare with other methods.\nThe critical side-wind was found using a simplified model of an accelerating rocket and tested on the full model. Since ballistic motion is always forward\, it is a common analytical practice to express some of the equations using downrange dist ance instead of time as the independent variable. This way\, some expressi ons become simpler and calculations are easier.\nA sensitivity study will be presented\, showing the critical side-wind that was found is indeed the critical boundary for a safe launch. Furthermore\, it is shown that an ae rodynamic controller can help widen the boundaries.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/97200263778 END:VEVENT BEGIN:VEVENT UID:0-9@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210107T183000 DTEND;TZID=Asia/Jerusalem:20210107T193000 DTSTAMP:20221030T083448Z URL:https://aerospace.technion.ac.il/events/year-end-ceremony-party/ SUMMARY:Year End Ceremony & Party DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Technion Amphi theatre / Faculty Main Hall\n Zoom: \n Abstract: \n Details: \n Graduation ceremony and year-end partyץ Class of 2019-2020 CATEGORIES:Events LOCATION:Technion Amphitheatre / Faculty Main Hall END:VEVENT BEGIN:VEVENT UID:0-270@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210111T123000 DTEND;TZID=Asia/Jerusalem:20210111T123000 DTSTAMP:20230525T064400Z URL:https://aerospace.technion.ac.il/events/simulation-of-the-dynamic-resp onse-of-aero-servo-elastic-wind-tunnel-model-to-non-uniform-gust/ SUMMARY:Simulation of the Dynamic Response of Aero-Servo-Elastic Wind-Tunne l Model to Non-Uniform Gust DESCRIPTION:Lecturer:Rami Veiberman\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: https://technion.zoom.us/j/91923136648\n Zoom: \n Abstract: \n Details: \n Simulation of dynamic response of Aero-Servo-Elastic Wind-Tunnel model to Non-Uniform gust was conducted. The research is done under the “Gust Lo ad Alleviation techniques assessment on wind tunnel Model of advanced Regi onal aircraft (GLAMOUR)” as part of the Clean Sky Joint Undertaking. Th e wind tunnel model simulated had non-linear actuators and the gust genera ted in the wind tunnel test was not uniform. The simulation was based upon the Increased Order Modeling (IOM) approach devised by Professor Karpel. Actuator force-feedback was modeled using the direct-force approach. Descr iption of the simulation model\, mathematical representation\, numerical r esults and their comparison to wind tunnel testing would be presented.\nZo om meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91923136648 END:VEVENT BEGIN:VEVENT UID:0-278@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210118T123000 DTEND;TZID=Asia/Jerusalem:20210118T133000 DTSTAMP:20230525T070702Z URL:https://aerospace.technion.ac.il/events/fluid-structure-interactions-w ith-flapping-compliant-membrane-wings/ SUMMARY:Fluid-Structure Interactions with Flapping\, Compliant Membrane Win gs DESCRIPTION:Lecturer:Gali Alon Tzezana\n Faculty:Center for Fluid Mechanics \, School of Engineering\n Institute:Brown University\n Location:https://t echnion.zoom.us/j/91638313889\n Zoom: \n Abstract: \n Details: \n Numerous animals including fish\, birds\, bats and insects use appendages (fins an d wings) with varying levels of flexibility\, to provide propulsion and/or weight support as they move through either air or water. Scientists have explored many different aspects of biological swimming and flying\, such as flapping and flexibility effects\, in an attempt to understand the unde rlying physical mechanisms and to apply them to engineering applications. Compliant membranes\, used by bats\, flying squirrels\, lemurs and other  animals define a specific subset of this class of flexible aerodynamic str uctures and is of particular interest due to their negligible thickness an d large shape deformations in both steady and unsteady conditions. This wo rk deals with the aerodynamic and hydrodynamic characteristics of a flapp ing\, compliant membrane wing. A theoretical framework is developed to cha racterize the effects of wing compliance\, inertia and flapping kinematics on the membrane's performance. As the flapping frequency is increased\,  membranes go through a transition from thrust to drag around the resonant frequency\, and this transition is earlier for more compliant membranes. T he limitations of the linear\, small-amplitude model are evaluated experim entally\, by testing different compliant membranes performing a heaving m otion in a water flume. Membrane deformations and force data show a resona nt peak close to the natural frequency of the membranes. Thrust is evaluat ed through direct measurement as well as wake analysis\, and the limitatio ns of both methods are discussed. The analytic model and the experimental data provide guidelines to finding membrane and motion parameters to opti mize the propulsive performance.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91638313889 END:VEVENT BEGIN:VEVENT UID:0-272@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210127T163000 DTEND;TZID=Asia/Jerusalem:20210127T173000 DTSTAMP:20230525T065128Z URL:https://aerospace.technion.ac.il/events/construction-of-non-equilibriu m-hydrodynamic-models-for-atmospheric-entry-plasmas/ SUMMARY:Construction of Non-Equilibrium Hydrodynamic Models for Atmospheric Entry Plasmas DESCRIPTION:Lecturer:Marco Panesi\n Faculty:Associate Professor in the Aero space Engineering Department and director of the Center for Hypersonics an d Entry System Studies (CHESS)\n Institute:University of Illinois at Urban a Champaign\n Location:https://technion.zoom.us/j/94086793352\n Zoom: \n A bstract: \n Details: \n The simulation of the aerothermal environment surr ounding vehicles moving at hypersonic speed is a complex problem due to it s multi-physics and multi-scale nature. Progress in the ability to accurat ely model these systems has been hindered by the lack of reliable physical and chemical models for collisional and radiative processes. Furthermore\ , the predictive capabilities of these models are often established by a s imple comparison of the model predictions against results from legacy expe rimental measurements\, the accuracy of which is often not well characteri zed. Substantial progress in the area of computational chemistry\, along w ith increased computational resources\, have allowed for the construction of realistic models based on molecular-scale dynamics. I propose to use st ate specific collisional radiative models as a powerful tool to derive mac roscopic conservation equations\, energy exchange terms and chemical produ ction rates for atmospheric entry plasmas. I will cover the key aspects in volved in model development\, namely: (1) using ab-initio quantum calculat ions as a powerful tool to construct high-fidelity physics-based models\; (2) defining reduced-order models for the simulation of 2D and 3D flows (e .g.\, coarse-grain modeling)\; (3) validating physical models and determin ing the uncertainty in their predictive capabilities\, based on the most r ecent developments in Uncertainty Quantification (UQ) algorithms.\n \; \n\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/94086793352 END:VEVENT BEGIN:VEVENT UID:0-277@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210203T163000 DTEND;TZID=Asia/Jerusalem:20210203T173000 DTSTAMP:20230525T070642Z URL:https://aerospace.technion.ac.il/events/preliminary-design-tool-for-op timal-effusion-cooling-holes-diameter-and-spacing/ SUMMARY:A Preliminary Design Tool for Optimal Effusion Cooling Holes Diamet er and Spacing DESCRIPTION:Lecturer:Yair Lange\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:http s://technion.zoom.us/j/91723342653\n Zoom: \n Abstract: \n Details: \n Mic ro gas turbines generally employ uncooled turbine blades and their thrust is limited by the maximum allowable gas temperature. A miniature cooling s cheme embodying effusion cooling may significantly enable higher thrust-to -weight ratios. Modern manufacturing capabilities are improving and enabli ng affordable solutions for innovative cooling techniques. In scope of thi s work\, a quasi 1D effusion cooling model is developed. The model conside rs the internal duct and effusion holes flow\, conjugate heat transfer and the external film coverage. Solid temperature is allowed to vary both in direction of metal shell thickness and the stream-wise direction of the ex ternal gas flow. The model is validated against three-dimensional computat ional fluid dynamics and it is shown that the model can predict main featu res of the combined internal and effusion cooling in gas turbine blades. A s a next step\, design optimization is conducted towards minimizing coolan t mass flow rate while retaining solid temperature at a prescribed value. Finally\, this coolant modeling scheme is implemented for micro gas turbin e blades in order to find the preferable effusion holes pitch and diameter distributions. This approach offers a potential to decouple turbine aerod ynamics\, which dictate the core\, from the thermal management provided by the shell. Therefore\, as the shell and core manufacturing processes are also separated\, the design timeline and development costs of the turbine stage can be reduced.\n \;\n\nZoom Meeting  CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91723342653 END:VEVENT BEGIN:VEVENT UID:0-273@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210215T123000 DTEND;TZID=Asia/Jerusalem:20210215T133000 DTSTAMP:20230525T065150Z URL:https://aerospace.technion.ac.il/events/measurement-and-assessment-of- aerodynamically-generated-noise-inside-an-airborne-structure/ SUMMARY:Measurement and assessment of aerodynamically generated noise insid e an airborne structure DESCRIPTION:Lecturer:Matan Mendelovich\n Faculty:Department of Aerospace En gineering\n Institute:Technion – Israel Institute of Technology\n Locati on:https://technion.zoom.us/j/99708099172\n Zoom: \n Abstract: \n Details: \n During the design phase of a project\, each airborne system is designe d and tested in order to demonstrate it can perform under different enviro nmental loads. Acoustic noise is one of the environmental loads that may l ead to a failure of the system - mainly in electronic equipment\, sensors\ , MEMS components etc. During the design\, the designer must take into acc ount the acoustic noise inside an airborne system in order to make sure th at the product can perform according to its requirements. A reliable tool is needed in order to define the acoustic noise level and spectrum inside an airborne structure. The aim of this thesis is to provide an algorithm t hat will allow estimation of the acoustic noise inside an airborne structu re. In order to do so\, the study is divided into two parts. One is estima tion of the external acoustic noise (wall pressure). Estimation of the ext ernal acoustic noise will enable the designer to perform FE simulation or to use different "thumb rules" in order to estimate the internal acoustic noise. It will also provide the designer the ability to perform laboratory acoustic noise tests\, in which he can simulate the external acoustic noi se outside the structure. On the second part\, an algorithm that allows es timation of the acoustic noise inside the structure based on the structure 's vibrations measurements will be suggested. In order to allow estimation of the external and internal noise\, this study is based on two experimen t's configurations. One is a wind tunnel experiment\, in which the suggest ed models and algorithms could be tested at different velocities and in co ntrolled environment. The second is a flight experiment\, in which the env ironmental conditions are more realistic then the wind tunnel experiment\, but much harder to control.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/99708099172 END:VEVENT BEGIN:VEVENT UID:0-276@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210217T163000 DTEND;TZID=Asia/Jerusalem:20210217T173000 DTSTAMP:20230525T070421Z URL:https://aerospace.technion.ac.il/events/automatic-landing-performance- of-a-civil-aircraft-in-the-presence-of-vertical-gusts/ SUMMARY:Automatic landing performance of a civil aircraft in the presence o f vertical gusts DESCRIPTION:Lecturer:Yaacov Eisenthal\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:https://technion.zoom.us/j/94464769758\n Zoom: \n Abstract: \n Details: \n The commercial aviation industry is motivated to continuously improve l anding performance without involving radical changes to aircraft design or operation. In the presence of strong gusts the landing is considered to b e one of the most complex and challenging maneuvers to perform correctly\, especially in large civil aircraft. It is a common knowledge that increas ing approach speed in gusty weather makes the task easier. In order to avo id the risk of runway overrun\, it is necessary to define what is the mini mal approach speed required for a particular gust profile and magnitude. I t also raises a question regarding the landing configuration: Can differen t flaps setting help?\nBoth of these questions are addressed using a reali stic 3DOF simulation of a DC-8 aircraft equipped with a generic automatic landing system as well as an angle of attack (AOA) protection and throttle limiter. It was found that keeping the flaps fully extended and increasin g the approach speed is beneficial in gusty conditions. Furthermore\, a qu antitative guideline is provided using a vertical gust limitation mapped a s a function of selected approach speed.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/94464769758 END:VEVENT BEGIN:VEVENT UID:0-258@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210222T123000 DTEND;TZID=Asia/Jerusalem:20210222T133000 DTSTAMP:20230525T063318Z URL:https://aerospace.technion.ac.il/events/nozzle-aerothermodynamic-desig n-for-a-plasma-heated-supersonic-wind-tunnel/ SUMMARY:Nozzle Aerothermodynamic Design for a Plasma Heated Supersonic Wind Tunnel DESCRIPTION:Lecturer:Nir Bratman\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:htt ps://technion.zoom.us/j/98199900410\n Zoom: \n Abstract: \n Details: \n Hi gh-enthalpy arc-heated supersonic wind tunnels are characterized by test g ases that are heated by a high-current electric arc and then expanded and accelerated through a convergent-divergent nozzle. In this work\, a Mach 4 supersonic nozzle was designed for the Technion Arc-Plasma wind Tunnel (T APT) according to two different working point conditions characterized by different plenum enthalpies and pressures. The objective was to obtain ide ally expanded gas with no shock wave formation at the nozzle exit and acco mpanying low nozzle temperatures. The initial design was performed using a simplified approach\, enabling the examination of feasible design paramet ers\, which were subsequently validated using CFD and finite element struc tural simulations. The simplified design approach was subdivided into an a erodynamic component (method of characteristics)\; semi-empirical aerodyna mic-heating predictions\;  empirical nozzle cooling-jacket performance pr edictions\; and structural considerations (based on the pressure and therm ally induced stresses). The simplified result showed excellent agreement w ith CFD predictions and finite element structural simulations. On this bas is\, a nozzle design procedure was proposed while taking relatively high s afety factors into account. The methodology developed in this work is inte nded to support the facility for all future nozzle designs.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/98199900410 END:VEVENT BEGIN:VEVENT UID:0-275@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210224T163000 DTEND;TZID=Asia/Jerusalem:20210224T173000 DTSTAMP:20230525T070354Z URL:https://aerospace.technion.ac.il/events/estimation-and-control-for-coo perative-slung-load-transportation-by-a-team-of-multirotors/ SUMMARY:Estimation and Control for Cooperative Slung Load Transportation by a Team of Multirotors DESCRIPTION:Lecturer:David Marcovici\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :https://technion.zoom.us/j/95034990472\n Zoom: \n Abstract: \n Details: \ n Multirotor UAVs are becoming widespread for both civil and military uses \, such as photography\, surveillance and payload transportation. A slung load system\, in which the payload is connected to several multirotors thr ough cables\, can be used as a modular payload transportation system\, all owing significantly heavier and larger payloads to be carried\, which cann ot be transported using a single multirotor. Control and coordination of s uch multirotor-payload systems is address in this study.\nThe current rese arch adopts a geometric control approach\, in which the nonlinear and coup led dynamics of the multirotors\, cables and payload can be explicitly inc orporated into control system design. Using three or more multirotors\, th is approach enables a full 6DOF (pose) tracking of the payload. An on-line optimization scheme is used to enable safe and efficient transport maneuv er\, in terms of collision avoidance between multirotors and efficient wei ght distribution.\nTo cope with high levels of parameter uncertainty\, whi ch is bound to exist in a system of this kind\, an on-line parameter ident ification scheme is used to identify the payload parameters\, namely its m ass\, moments of inertia\, and cable connection points. It is shown that s ystem parameter identification and thus the reduction in parameter uncerta inty contributes greatly to the robustness and tracking performance of the system.\nPayload transportation using four Pegasus 120 octorotors of Aero nautics Ltd. is examined in a full scale 3D simulation\, demonstrating tha t the suggested approach provides excellent payload pose tracking\, even w hen the system is exposed to significant disturbances\, measurement noise and various uncertainties.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/95034990472 END:VEVENT BEGIN:VEVENT UID:0-260@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210301T123000 DTEND;TZID=Asia/Jerusalem:20210301T133000 DTSTAMP:20230525T063547Z URL:https://aerospace.technion.ac.il/events/experimental-aeroelastic-shape -sensing-and-control/ SUMMARY:Experimental Aeroelastic Shape Sensing and Control DESCRIPTION:Lecturer:Michael Simbuerger\n Faculty:Department of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion: https://technion.zoom.us/j/6068424887\n Zoom: \n Abstract: \n Detail s: \n The main goals in aircraft design nowadays are noise and emission re duction\, together with performance improvement.  These can be achieved s traightforwardly with lightweight\, large-span configurations. However\, l ight aircraft are inherently more flexible and susceptible to adverse aero elastic phenomena such as flutter\, reduced control-surface efficiency\, a nd large static and dynamic loads. Over the years\, and with advances in a ircraft control technology\, several studies have shown that wings' flexib ility can be leveraged to achieve optimal performance (e.g.\, drag reducti on\, minimization of loads\, or minimization of deformations) while minimi zing adverse aeroelastic effects.\nThe current research study focuses on d eveloping and implementing an aeroelastic shape sensing and control method ology that relies on strain-data from fiber-optic sensors (FOS).  Fiber-o ptic sensing is commonly used in civil engineering\, aerospace\, marine\, and oil and gas. Prominent use of fiber-optic sensors (FOS) in the aerospa ce industry is for structural health monitoring of complex aero-structures . FOS's inherent capabilities include strain accuracy\, spatial resolution \, broad strain dynamic range\, high sampling rate\, insensitivity to elec tromagnetic radiation\, small size\, and lightweight. These properties mak e FOS highly suitable for aerospace systems.  Recent studies demonstrated how FOS strain-data could be used to reconstruct the static and dynamic d eformed shape of a flexible wing and predict the flutter onset speed. The current study further develops these capabilities and demonstrates wing-sh ape control based on strain-data measured via FOS.\nThe seminar will prese nt the wing design\, analyses\, instrumentation with optical fibers\, and experiments. FOS-based trim optimization was successfully realized\, reduc ing the wing's deformation by 30% while maintaining a required nominal lif t.\nhttps://technion.zoom.us/j/6068424887 CATEGORIES:Seminars LOCATION: https://technion.zoom.us/j/6068424887 END:VEVENT BEGIN:VEVENT UID:0-240@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210303T163000 DTEND;TZID=Asia/Jerusalem:20210303T173000 DTSTAMP:20230417T065903Z URL:https://aerospace.technion.ac.il/events/experimentation-inlet-isolator -and-combustor-physics-in-scramjets/ SUMMARY:Experimentation: Inlet Isolator and Combustor Physics in Scramjets DESCRIPTION:Lecturer:Prof. Tonghun Lee\n Faculty:Department of Mechanical S cience & Engineering\n Institute:University of Illinois Urbana-Champaign\n Location:https://technion.zoom.us/j/94032426223\n Zoom: \n Abstract: \n D etails: \n This talk outlines an effort to understand the impact of inlet isolator physics on the combustion of scramjet engines under actual flight relevant high speed conditions. The objective of the proposed work is to gain a fundamental understanding of the feedback mechanism between the bou ndary layer structures and separated flow in the isolator and the correspo nding combustion dynamics that can lead to instabilities and/or unstart. A n experimental effort is presented where unstart and combustion instabilit ies are investigated in an optically accessible axisymmetric scramjet mode l in a free flow high enthalpy flow tunnel (ACT-II). The effort is coupled with advanced spatially resolved diagnostics of both the isolator and the combustor region to obtain critical insight into the key physics\, and to provide foundational data for numerical simulation efforts.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/94032426223 END:VEVENT BEGIN:VEVENT UID:0-261@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210310T163000 DTEND;TZID=Asia/Jerusalem:20210310T173000 DTSTAMP:20230525T063613Z URL:https://aerospace.technion.ac.il/events/low-cost-aerial-platform-for-g uidance-navigation-and-control-system-design/ SUMMARY:Low-Cost Aerial Platform for Guidance\, Navigation and Control Syst em Design DESCRIPTION:Lecturer:Nathaniel Drellich\n Faculty:Department of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:https://technion.zoom.us/j/98147174075\n Zoom: \n Abstract: \n Details : \n In a general research setting\, theoretical models combined with simu lation provide the backbone for guidance\, navigation\, and control system s design. While these are both powerful tools to represent physical system s\, they are inferior replacements to practical implementation on physical hardware. However\, a myriad of factors often prevents such implementatio n. These include\, but are not limited to\, the high cost of hardware\, us er-unfriendly interfaces\, and systems not being designed for ease of modi fication of software or hardware.\nThe goal of this research was to provid e a low-cost solution to this problem. In this talk\, we describe the deve lopment of such a platform that includes the design of a 3D-printable quad rotor aerial vehicle with inexpensive off-the-shelf components\, user-frie ndly flight controller software (including guidance\, navigation\, and con trol modules)\, a modular six degree of freedom simulation environment\, a nd physical hardware for use in testing the quadrotor in a safe manner pri or to free flight. A demonstration of the complete platform will be presen ted.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/98147174075 END:VEVENT BEGIN:VEVENT UID:0-259@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210315T123000 DTEND;TZID=Asia/Jerusalem:20210315T133000 DTSTAMP:20230525T063523Z URL:https://aerospace.technion.ac.il/events/on-the-operation-of-a-microjet -engines-vaporizer-under-steady-state-conditions/ SUMMARY:On the operation of a microjet engine's vaporizer under steady-stat e conditions DESCRIPTION:Lecturer:Ori Kam\n Faculty:Department of Aerospace Engineering\ n Institute:Technion – Israel Institute of Technology\n Location:https:/ /technion.zoom.us/j/95787017110?pwd=WXFoN1pIZzFiaUVrcE5PallrTWpIUT09\n Zoo m: \n Abstract: \n Details: \n Fuel supply in microjet engines typically m akes use of fuel vaporizers. These have a simple design however\, their op eration involves complicated physics including the disintegration of liqui d jet under co-flowing air\, impingement of liquid jet on hot wall\, forma tion and motion of liquid film\, droplet splashing and fuel evaporation oc curring over different two-phase flow regimes. The objective of the presen ted study is to investigate these processes and develop physical models to evaluate the fuel evaporation rate. The work involved a coupled analytica l – experimental study of the disintegration of liquid jet\, the impinge ment process and the heat transfer between combustion gases and a the two phase flow within a tube exposed to these gases. A major effort was invest ed to develop the experimental setup for these studies that included a swi rl stabilized kerosene fueled combustor with a crossing metal tube in whic h fuel and air were supplied under conditions complying with the flow in a typical vaporizer. The vaporization rate was measured by deducting the co llected fuel at the exit of the tube from the inlet flow rate after its se paration from the flowing gaseous phase (air &\; fuel vapor). The main result indicated that the evaporation is very sensitive to the inlet fuel to air mass flow ratio. Hence\, by modifying the fuel to air mass flow rat io\, one can control the vaporizer performance and improve the combustion efficiency and the global engine performance.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/95787017110?pwd=WXFoN1pIZzFiaUVrcE5Pall rTWpIUT09 END:VEVENT BEGIN:VEVENT UID:0-264@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210317T163000 DTEND;TZID=Asia/Jerusalem:20210317T173000 DTSTAMP:20230525T063734Z URL:https://aerospace.technion.ac.il/events/transportation-of-a-slung-load -using-multiple-multirotors-while-maintaining-a-constant-altitude-above-th e-terrain/ SUMMARY:Transportation of a Slung Load Using Multiple Multirotors While Mai ntaining a Constant Altitude Above the Terrain DESCRIPTION:Lecturer:Tomer Levy\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:http s://technion.zoom.us/j/99906260343\n Zoom: \n Abstract: \n Details: \n In recent years\, the use of multi-rotors has been drastically increased both in military and civil applications. Specifically\, load transportation us ing a flock of rotary unmanned aerial vehicles (UAVs) has been widely stud ied and developed in the last decade. Carrying a load using multiple UAVs allows to significantly increase the maximum weight that can be carried.\n Beyond the challenge of controlling the multi-UAV connected to a load syst em\, the ability to keep the load at constant altitude above the terrain e xposes us to a field of autonomous complex maneuvers which is attractive f or a wide range of applications. In this study we incorporate the terrain following capability into a multi-UAV connected to a load system\, which w as not addressed in the open literature.\nThis research revolves around th e development of a control algorithm that will allow the safe transportati on of a load using a team of three or more octorotors as actuators. The al gorithm accounts for different constraints such as safety distance between the octorotors\, maximum allowed force each octorotor can provide\, and m ore. The system incorporates a terrain following capability that relies on measurements received from body-fixed Laser Range Finder (LRF) sensors in stalled on the octorotors.\nThe algorithm was validated and tested for dif ferent scenarios using a realistic 6DOF simulation that incorporates distu rbances\, measurement noises and model inaccuracies. A parametric study wa s conducted in order to determine the optimal configuration of the LRF sen sors and to examine parameter sensitivity of the setup. The system has dem onstrated impressive performance characteristics for a variety of flight c onditions.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/99906260343 END:VEVENT BEGIN:VEVENT UID:0-263@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210322T123000 DTEND;TZID=Asia/Jerusalem:20210322T133000 DTSTAMP:20230525T063708Z URL:https://aerospace.technion.ac.il/events/autonomous-classification-unde r-uncertainty/ SUMMARY:Autonomous Classification Under Uncertainty DESCRIPTION:Lecturer:Vladimir Tchuiev\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:https://technion.zoom.us/j/95387827267\n Zoom: \n Abstract: \n Details: \n Classification and object recognition is a fundamental problem in many robotics and aerospace applications\, such as autonomous driving\, vision- based navigation\, and search &\; rescue.\nThe field has advanced much in recent years with the introduction of deep-learning-based approaches\, yet reliable classification remains a significant problem. Classification results may be\naffected by varying viewpoints\, changing lighting conditi ons\, occlusions\, localization uncertainty\, and limited by the classifie r's training set. In this work\, we propose several sequential classificat ion approaches that deal with some of these uncertainties within a semanti c simultaneous localization and mapping (SLAM) framework.\nFirst\, we prop ose using a viewpoint-dependent classifier model\, which uses the coupling between object class and pose to assist in addressing classification and perceptual aliasing. We do so by maintaining a hybrid belief over continuo us and discrete random variables. One robot may prove insufficient in clas sifying the objects within the environment\, so we propose a formulation t hat uses the viewpoint-dependent model within a distributed multi-robot se tting\, while keeping the estimation consistent for both continuous and di screte random variables. Furthermore\,\nthe classifier's training set is l imited\, and during deployment the robot may encounter scenarios in which it was not trained on\, inducing epistemic uncertainty. We propose a seque ntial classification approach that accounts for posterior epistemic uncert ainty from a sequence of images. Eventually\, we incorporate posterior epi stemic uncertainty within a belief space planning (BSP) framework\, consid ering in particular autonomous classification and active semantic SLAM. We study our approaches in simulation and using real data.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/95387827267 END:VEVENT BEGIN:VEVENT UID:0-256@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210324T163000 DTEND;TZID=Asia/Jerusalem:20210324T173000 DTSTAMP:20230525T063225Z URL:https://aerospace.technion.ac.il/events/plasma-generation-and-accelera tion-mechanisms-in-capillary-capacitive-coupled-radio-frequency-thruster/ SUMMARY:Plasma Generation and Acceleration Mechanisms in Capillary Capaciti ve Coupled Radio-Frequency Thruster DESCRIPTION:Lecturer:Arsad Quraishi\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: https://technion.zoom.us/j/8167918651\n Zoom: \n Abstract: \n Details: \n Capacitively coupled radio-frequency thrusters (CCRFT) are an attractive p ropulsion option for nanosatellites due to their low operating power\, rel atively high thrust\, and low erosion of the electrodes. Such thrusters ca n serve as a direct replacement to cold gas thrusters\, achieving higher s pecific impulse. CCRFTs produce thrust by generating a gaseous electric di scharge within a dielectric tube by means of RF power. The RF circuit coup les to the plasma via a capacitor therefore blocking the dc current compon ent. The discharge heats the gas inside the tube\, and the heated gas is e jected from the tube tip or nozzle to produce thrust.\n A capillary capac itively coupled radio-frequency thruster (C3RFT) is being developed at the Aerospace Plasma Laboratory\, Technion. The small diameter of the dielect ric tube allows operation of the device in very low flow rates 4-16 SCCM i n Ar. The thruster utilizes a non-symmetric electrode arrangement and no n ozzle. At constant input power\, the thrust is shown to increase linearly with the flow rate. At an input power of 14 W and a flow rate of 8 SCCM\, the thrust increases significantly by 60 % compared to the cold flow case\ , for a total thrust of ≈ 160 µN and specific impulse ≈ 70 s in Ar.\n The C3RFT discharge is shown to be sensitive to electrode polarity. When t he larger back electrode is powered and the front electrode grounded a mod e transition of the discharge is observed. This phenomenon is marked by an appearance of bright plasma exhaust and reduction in input power from ≈ 15.17 W to ≈ 9 W. After the transition\, the thrust to power ratio incr eases by 25 %. A sheath breakdown model is proposed to explain this transi tion. The thrust can be completely attributed to gas dynamic acceleration. \nComputational fluid dynamics (CFD) plasma simulations were performed to analyze the spatial characteristics of the discharge in the C3RFT. The sim ulated thruster performance is found to be in good agreement with measurem ents. For a grounded back electrode case\, the plasma potential is found t o drop near the smaller front powered electrode creating a negative DC bia s\, in accordance with classical theory of asymmetric capacitive discharge . Electrons in sheath are heated to ~ 6 eV whereas in the rest of the capi llary the electron temperature ~ 2 eV. The plasma density is 1019 m-3 wher eas excited argon species are 1020 m-3.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/8167918651 END:VEVENT BEGIN:VEVENT UID:0-241@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210405T123000 DTEND;TZID=Asia/Jerusalem:20210405T133000 DTSTAMP:20230417T065952Z URL:https://aerospace.technion.ac.il/events/optimization-of-energy-distrib ution-in-nanosecond-pulsed-high-frequency-discharge-ignition/ SUMMARY:Optimization of Energy Distribution in Nanosecond-Pulsed High-Frequ ency Discharge Ignition DESCRIPTION:Lecturer:Iker Laso\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:https ://technion.zoom.us/j/98684528360\n Zoom: \n Abstract: \n Details: \n Igni tion is a challenge for gas turbines\, ramjets and scramjets where flow ve locities in the combustor are high\, resulting in short flow residence tim es. The success of ignition depends on the flow conditions\, as well as th e ignition method. In the past years\, nanosecond-pulsed high-frequency di scharge (NPHFD) plasmas have been pointed out as an optimal alternative ig nition method in flowing mixtures\, given that they offer several advantag es as compared to a long duration DC discharge. Previous works have shown that the interaction between subsequent ignition kernels lead to three dif ferent coupling regimes based on their ignition probability (PI): fully-co upled (highest PI)\, partially-coupled (lowest PI) and decoupled (PI linea rly dependent on the number of pulses)\, which occur at different inter-pu lse time conditions.\nIn the current research\, a new experimental platfor m has been built to explore NPHFD ignition. It has been found that the PI of the aforementioned regimes can be altered by varying the energy per pul se (Epp). In fact\, high Epp has resulted in the disappearance of the part ially-coupled regime\, and low Epp has proven a negligible PI except for t he fully-coupled regime. It has also been found that the minimum ignition power – defined as the applied power that results in 50% of PI – decre ases linearly as the Epp is lowered. The kernel-growth rate has been found similar in all the tested cases.\nAdditionally\, energy distribution has been optimized by matching the total energy and time of the discharge\, an d varying the number of pulses and the Epp. It has been concluded that the inter-pulse time is the driving parameter of the ignition probability. In deed\, it has been observed that low total energy and long total time disc harges can provide a high PI at the right IPT.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/98684528360 END:VEVENT BEGIN:VEVENT UID:0-267@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210407T163000 DTEND;TZID=Asia/Jerusalem:20210407T173000 DTSTAMP:20230525T064159Z URL:https://aerospace.technion.ac.il/events/modeling-prediction-and-mitiga tion-of-nonlinear-complex-dynamical-systems-under-stochastic-disturbances/ SUMMARY:Modeling\, Prediction\, and Mitigation of Nonlinear Complex Dynamic al Systems Under Stochastic Disturbances DESCRIPTION:Lecturer:Maor Farid\n Faculty:Mechanical Engineering\, MIT\; Me chanical Engineering\, Technion\n Institute:Mechanical Engineering\, MIT\; Mechanical Engineering\, Technion\n Location:https://technion.zoom.us/j/9 3324438721\n Zoom: \n Abstract: \n Details: \n Destructive vibrations caus ed by stochastic external disturbances such as earthquakes\, explosions\, and fluid-structure interactions pose an insidious threat to various criti cal infrastructure and mechanical components. Among the most vulnerable an d potentially hazardous are large structures\, nuclear facilities\, aerosp ace\, and naval vehicles. Damage to these systems not only might endanger human lives but also often result in long-term environmental and ecologica l distress. Hence\, reliable models for real-time prediction of the dynami cal responses and resulting stresses under stochastic excitations are a cr itical necessity for the operation\, maintenance\, and structural health m onitoring of these systems. However\, most of the aforementioned systems c onsist of numerous smaller elements of various shapes and physical propert ies—hence they are referred to as complex systems—which are a great ch allenge to model and predict. Therefore\, the vast majority of existing pr ediction methods are based on either over-simplistic models that suffer fr om poor accuracy\, or time-consuming computational models that are not app licable for real-time purposes and do not describe the underlying mechanis ms that govern the system’s dynamical response.\nThe current research fo cuses on a multidisciplinary approach\, combining both reduced-order model ing and machine-learning-based methods for the description and prediction of complex dynamical systems. Finally\, hybrid vibration mitigation soluti ons are introduced\, which utilize both linear and nonlinear energy absorp tion techniques for enhanced protection capabilities. The methods presente d pave the way towards faster and more accurate forecasting methods as wel l as more effective vibration mitigation technologies\, allowing for enhan ced resistance of existing facilities\, structures\, and mechanical compon ents to a variety of external disturbances in real-time. Thus\, they are o f great importance in terms of public health\, homeland security\, and env ironmental responsibility.\nThis work is funded by the Fulbright program\, the ISEF Foundation\, the Israel Academy of Sciences and Humanities\, the Shamir Scholarship of the Israeli Ministry of Science\, Technology\, and Space\, and the PMRI -Technion.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/93324438721 END:VEVENT BEGIN:VEVENT UID:0-265@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210412T163000 DTEND;TZID=Asia/Jerusalem:20210412T173000 DTSTAMP:20230525T063758Z URL:https://aerospace.technion.ac.il/events/combustion-dynamics-of-an-acou stically-excited-scramjet-engine/ SUMMARY:Combustion Dynamics of an Acoustically Excited Scramjet Engine DESCRIPTION:Lecturer:Neta Yokev\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:http s://technion.zoom.us/j/95894901855\n Zoom: \n Abstract: \n Details: \n The supersonic combustion ramjet\, or scramjet\, is an air-breathing engine d esigned for cruise at Mach number of 5 and above. The high-speed flow with in the combustor poses a major issue with regard to combustion\, because t he air and fuel must mix and ignite within a time frame of typically less than 1 millisecond. This makes flame anchoring and efficient combustion ve ry difficult. Moreover\, due to the elevated air stagnation temperatures a t flight of high Mach number\, thermal management becomes a big challenge. This study addresses these three topics using a new experimental setup.\n             It was found that it is possible to alter the flame stabilization mode by distributing the fuel between two fuel injectors\, one in the cavity and one upstream of the cavity. When a sufficiently high fuel flow rate in the cavity led to flame stabilization in the fuel jet ’s wake\, and a more confined combustion zone. Shadowgraph imaging showe d that injection of the fuel from the cavity floor at a sufficient momentu m penetrated the shear layer over the cavity and enabled flame propagation upstream of the cavity. It was concluded that the heat release distributi on and pressure profile in the combustor could be significantly influenced by the fuel injection distribution through its impact on the flame stabil ization mode.\nIn addition to hydrocarbon gaseous fuel (ethylene)\, simula ted synthetic gas (mixture of hydrogen and methane) was used. Syngas is a product of an endothermic chemical reaction between water and hydrocarbon fuel\, called steam reforming\, enabling up to 3 times higher heat sink th an fuel cracking. It was found that the simulated syngas did not burn on i ts own in the supersonic chamber due to the relatively long ignition delay of the methane-hydrogen mixture compared to ethylene.\nForced acoustic ex citation was investigated as a method for mixing enhancement in scramjet e ngines for the first time.  It was found that acoustic forcing at frequen cies of below ~100 Hz during transition between 2 combustion modes led to a higher probability of the more efficient combustion mode. This led to an average pressure-rise of 14% compared the non-excited baseline. Analysis of the chemiluminescence and pressure data suggested that the acoustic for cing excited heat release oscillations at ~10 Hz at the cavity shear layer \, which were enhanced further downstream leading to a more efficient comb ustion.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/95894901855 END:VEVENT BEGIN:VEVENT UID:0-266@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210419T123000 DTEND;TZID=Asia/Jerusalem:20210419T133000 DTSTAMP:20230525T064132Z URL:https://aerospace.technion.ac.il/events/development-of-combustion-meas urement-technique-in-the-infrared-spectrum/ SUMMARY:Development of combustion measurement technique in the infrared spe ctrum DESCRIPTION:Lecturer:Karin Linshitz\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: https://technion.zoom.us/j/97444605489\n Zoom: \n Abstract: \n Details: \n Investigation of the performance of experimental combustion devices relie s heavily on proper diagnostics for characterization of operating regimes and validation of numerical modelling predictions. The primary goal of thi s work is to develop and implement a measurement system using infrared (IR ) spectrum for measurements in combustion environments\, capable of making high repetition rate multi-parameter measurements at multiple locations. We use tunable diode laser absorption spectroscopy (TDLAS) in the mid-IR t o develop the capability of species and temperature measurements and use t his method to characterize a typical flame (Hencken Burner) as well as th e exit plane of a model scramjet engine. The measurement targets of prima ry interest are H2O concentration and flame temperature\, although the des igned system is also capable of NO\, CO2\, and CH2O concentration measurem ents. The design and assembly of the laser system is described in detail\, with specific attention given to selection of the proper laser wavelength s for detection of the four abovementioned species. The spectroscopic mode ling is described\, and a code utilizing known transition parameters is de veloped to quantify the collected data. Validation results in the Hencken burner demonstrate successful implementation of the measurement technique. Finally\, results collected in a scramjet test firing are presented. Expe riments using several ethylene fueling strategies were carried out in the scramjet combustor in the Fine Rocket Propulsion Laboratory\, and measurem ents of H2O concentration and temperature were taken at the exit plane.  Challenges of the implemented measurement technique and future directions for increased accuracy are addressed.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/97444605489 END:VEVENT BEGIN:VEVENT UID:0-257@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210421T163000 DTEND;TZID=Asia/Jerusalem:20210421T173000 DTSTAMP:20230525T063249Z URL:https://aerospace.technion.ac.il/events/hardware-in-the-loop-simulatio n-testbed-of-a-low-cost-research-missile/ SUMMARY:Hardware-in-the-Loop Simulation Testbed of a Low-Cost Research Miss ile DESCRIPTION:Lecturer:Guy Nevo\n Faculty:Department of Aerospace Engineering \n Institute:Technion – Israel Institute of Technology\n Location:https: //technion.zoom.us/j/97878357485?pwd=amVFOGpnZGJMM3l4N0gwakY4RWJoQT09\n Zo om: \n Abstract: \n Details: \n A crucial part of the development of a com plex system is its testing and validation. To support the design and valid ation process of a low-cost research missile\, a hardware-in-the-loop test bed was created.\nThe testbed is an invaluable tool for studying the behav ior of the missile in the lab in real-time and allows the testing and veri fication of the avionics\, ensuring they are working as intended before th e assembly and launching of the final product. Included in the list of har dware is the flight control computer\, with its custom software and GNC al gorithms\, a three-axis flight table to emulate the rotations of the missi le as would be in-flight\, an inertial measurement unit (IMU) to measure t hese rotations\, four servos to create fin deflections for steering the mi ssile\, and optical encoders to measure these deflections. The hybrid simu lation integrates these components with a mathematical model of the missil e’s flight dynamics. The flight computer\, IMU\, and servos are also emu lated in the simulation\, allowing us to test in an offline mode\, and to compare the performance of a physical module with its theoretical counterp art.\nThe design process of the testbed is described\, and results of both hybrid and offline simulations are presented\, along with a comparison be tween the two. Limitations of the testbed will be discussed\, and future a dditions and improvements will be suggested.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/97878357485?pwd=amVFOGpnZGJMM3l4N0gwakY 4RWJoQT09 END:VEVENT BEGIN:VEVENT UID:0-262@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210426T123000 DTEND;TZID=Asia/Jerusalem:20210426T133000 DTSTAMP:20230525T063642Z URL:https://aerospace.technion.ac.il/events/thrust-vectoring-and-after-bur ner-system-for-increasing-survivability-of-micro-jet-uavs/ SUMMARY:Thrust Vectoring and After Burner System for Increasing Survivabili ty of Micro-Jet UAVs DESCRIPTION:Lecturer:Dor Shitrit\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:htt ps://technion.zoom.us/j/92658464337\n Zoom: \n Abstract: \n Details: \n A major current threat on Unmanned Aerial Vehicles (UAVs) and Air-to-Surface Missiles (ASM) is being intercepted by Surface-to-Air Missiles (SAMs) wit h maneuvering capabilities. There are many methods to increase the surviva bility of such UAV and ASM while the challenge is keeping them cost-effect ive and relevant to the modern battlefield.\nOne of the ways to increase s urvivability is by improving agility. Agility of an aircraft can be improv ed by using thrust vectoring and activation of an after burner. It enables the platform to accelerate by operating the aft burner while vectorizing the thrust -thus “breaking lock” from the potential threat.\nThis stud y aims to investigate such integration in micro turbo jet UAVs. It include s dynamic simulation of the after burner as well as the vectoring nozzle s ystems and their effect on the aircraft overall performance. A total of 3 engine power configurations (basic with constant nozzle\, adjustable nozzl e\, adjustable nozzle with aft burner) and 2 vectoring configurations (wit h/without) are examined.\nFor this purpose\, Dornier "DT-45" UAV and "SA7- Strella" SAM are chosen as target and interceptor demonstrators. Whole eng ine decks are created including designing engine control system to withsta nd the engine limitations during the transient state. Drag polar\, stabili ty &\; control derivations of the target and interceptor main character istics are estimated. Evasive maneuver is characterized\, and a dedicated aircraft control system is implemented to support it.  Finally\, a quanti tative analysis for the joint contribution of thrust vectoring and after b urner to the survivability of the aircraft is introduced by implementation of interception simulation.\nZoom meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/92658464337 END:VEVENT BEGIN:VEVENT UID:0-62@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210505T123000 DTEND;TZID=Asia/Jerusalem:20210505T123000 DTSTAMP:20221031T074835Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%a4%d7%99%d7%a7%d7 %a0%d7%99%d7%a7-%d7%94%d7%a4%d7%a7%d7%95%d7%9c%d7%98%d7%99-2021/ SUMMARY:הפיקניק הפקולטי 2021 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:דשא הפקול טה\n Zoom: \n Abstract: \n Details: \n מוזמנים לפיקניק ה פקולטי השנתי. CATEGORIES:אירועים LOCATION:דשא הפקולטה END:VEVENT BEGIN:VEVENT UID:0-52@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210505T123000 DTEND;TZID=Asia/Jerusalem:20210505T143000 DTSTAMP:20221030T083449Z URL:https://aerospace.technion.ac.il/events/the-annual-faculty-picnic/ SUMMARY:The annual faculty picnic DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty Garden \n Zoom: \n Abstract: \n Details: \n CATEGORIES:Events LOCATION:Faculty Garden END:VEVENT BEGIN:VEVENT UID:0-255@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210519T163000 DTEND;TZID=Asia/Jerusalem:20210519T173000 DTSTAMP:20230525T061918Z URL:https://aerospace.technion.ac.il/events/asymptotic-theory-of-grid-fins / SUMMARY:Asymptotic theory of grid fins DESCRIPTION:Lecturer:Guy Levi\n Faculty:Department of Aerospace Engineering \n Institute:Technion – Israel Institute of Technology\n Location:https: //technion.zoom.us/j/92132513390\n Zoom: \n Abstract: \n Details: \n Grid fins are actually an array of short lifting surfaces arranged in a lattice . They appeared in engineering literature in the late eighties of the last century\, but they have probably been used in Russian military since late seventies. Notable current applications of these fins are found with the Falcon 9 launch vehicle\, Soyuz ground escape capsule\, and gliding weapon s. Notwithstanding their high drag\, they represent a viable alternative t o conventional fins because they fold easily\, have small hinge moment (be cause of their short chord length)\, are easy to manufacture\, and have hi gh strength to weight ratio.\nIn this study we develop an analytical aerod ynamic theory of grid fins in subsonic flow. The solution is based on a nu mber of small parameters of the problem\, the most conspicuous of which ar e the ratio of the fin chord to its span\, and the reciprocal of the numbe r of the fin’s lifting surfaces. It is shown that even in the leading or der approximation\, the theory fits well both numerical simulations based on the vortex lattice method and the available experimental data.\nZoom Me eting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/92132513390 END:VEVENT BEGIN:VEVENT UID:0-233@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210526T163000 DTEND;TZID=Asia/Jerusalem:20210526T173000 DTSTAMP:20230409T143539Z URL:https://aerospace.technion.ac.il/events/using-weakly-electric-fish-to- study-sensing-localization-and-mapping/ SUMMARY:Using weakly electric fish to study sensing\, localization and mapp ing DESCRIPTION:Lecturer:Avner Wallach\, Ph.D.\n Faculty:Zuckerman Institute of Mind\, Brain and Behavior\,\n Institute:Columbia University\, NY\n Locati on:https://columbiauniversity.zoom.us/j/96954362879?pwd=YkVmSlpseEJBK0RMTG Y2KzJuMVl6UT09\n Zoom: \n Abstract: \n Details: \n Through natural selecti on\, animals evolved the abilities required to survive in a complex dynami c world: they accurately perceive their surroundings\, map their environme nt and localize themselves and others within it\, develop flexible policie s to achieve various goals\, and translate these policies into motor actio ns. The natural mechanisms executing these tasks outperform currently exis ting artificial systems. They are implemented in hierarchical networks of closed circuits composed of complex non-linear dynamic elements – neuron s and synapses. In this talk\, I will show how frameworks and tools of eng ineering are used to investigate these mechanisms in the weakly electric f ish\, an animal that provides unparalleled access to the study of sensing\ , learning\, and control in three-dimensional space. A novel method I deve loped enables continuous\, long-term recording of motor\, sensory and neur onal signals in freely swimming fish. I used this method to study a brain circuit implementing an internal forward model involved in Adaptive Noise Cancelation of incoming sensory signals. I have found that such cancelatio n is critical to the animal’s ability to perceive and that its implement ation requires both motor command and sensory feedback signals. I will dis cuss future directions related to how the brain constructs an internal map of the environment and localize within it. Insights generated about these processes in natural systems will be used to advance artificial sensing a nd autonomy in terrestrial\, aquatic\, or aerial systems.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://columbiauniversity.zoom.us/j/96954362879?pwd=YkVmSlpseEJBK 0RMTGY2KzJuMVl6UT09 END:VEVENT BEGIN:VEVENT UID:0-61@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210602T123000 DTEND;TZID=Asia/Jerusalem:20210602T144500 DTSTAMP:20221031T073833Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%9e%d 7%97%d7%a7%d7%a8/ SUMMARY:יום מחקר DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:דשא הפקול טה\n Zoom: \n Abstract: \n Details: \n אתם מוזמנים להצגת פעילות מחקרי המשתלמים לתארים גבוהים בפק ולטה להנדסת אוירונוטיקה וחלל\n\n הצגת פוס טרים של משתלמים בפקולטה\n מידע למתענייני ם בתארים מתקדמים\n פיצה ובירה 🍺🍕 בדשא ה פקולטה\n CATEGORIES:אירועים LOCATION:דשא הפקולטה END:VEVENT BEGIN:VEVENT UID:0-234@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210623T163000 DTEND;TZID=Asia/Jerusalem:20210623T173000 DTSTAMP:20230409T143701Z URL:https://aerospace.technion.ac.il/events/merchav-prize-seminar-epistemi c-uncertainty-aware-semantic-localization-and-mapping-for-inference-and-be lief-space-planning/ SUMMARY:Merchav Prize Seminar | Epistemic Uncertainty Aware Semantic Locali zation and Mapping for Inference and Belief Space Planning DESCRIPTION:Lecturer:Vladimir Tchuiev\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr act: \n Details: \n We investigate the problem of autonomous object classi fication and semantic SLAM\, which in general exhibits a tight coupling be tween classification\, metric SLAM and planning under uncertainty. We cont ribute a unified framework for inference and belief space planning (BSP) t hat addresses prominent sources of uncertainty in this context: classifica tion aliasing (classier cannot distinguish between candidate classes from certain viewpoints)\, classifier epistemic uncertainty (classifier receive s data "far" from its training set)\, and localization uncertainty (camera and object poses are uncertain). Specifically\, we develop two methods fo r maintaining a joint distribution over robot and object poses\, and over posterior class probability vector that considers epistemic uncertainty in a Bayesian fashion. The first approach is Multi-Hybrid (MH)\, where multi ple hybrid beliefs over poses and classes are maintained to approximate th e joint belief over poses and posterior class probability. The second appr oach is Joint Lambda Pose (JLP)\, where the joint belief is maintained dir ectly using a novel JLP factor. Furthermore\, we extend both methods to BS P\, planning while reasoning about future posterior epistemic uncertainty indirectly\, or directly via a novel information-theoretic reward function . Both inference methods utilize a novel viewpoint-dependent classifier un certainty model that leverages the coupling between poses and classificati on scores and predicts the epistemic uncertainty from certain viewpoints. In addition\, this model is used to generate predicted measurements during planning. To the best of our knowledge\, this is the first work that reas ons about classifier epistemic uncertainty within semantic SLAM and BSP. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-235@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210623T163000 DTEND;TZID=Asia/Jerusalem:20210623T173000 DTSTAMP:20230410T063653Z URL:https://aerospace.technion.ac.il/events/merchav-prize-seminar-a-nonlin ear-diagnostic-for-scale-interactions-in-turbulent-flows/ SUMMARY:Merchav Prize Seminar | A Nonlinear Diagnostic for Scale Interactio ns in Turbulent Flows DESCRIPTION:Lecturer:Guangyao Cui\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Turbulent flows are composed of a wide range of large- and small-scale coherent motions. These motions are responsible for practical engineering effects\, like the generation of turbulent drag. Scale intera ctions between large- and small-scales in turbulent wall-bounded flows hav e historically been investigated by linear analysis which requires a filte ring and envelope procedure. The phase delay between large and envelope of small scales was explained as a spatial delay in the flow. However\, the linear analysis depends on the cutoff wavelength in the filtering process and the use of an artificial envelope of small scales that does not exist in real data. The Fourier transformed momentum equation shows that only th e nonlinear advection term contributes to the interaction among different scales and thus all interactions occur in triads. A nonlinear diagnostic\, the bispectrum\, is introduced and applied to a numerical turbulent chann el flow. The bispectrum shows that large-scale structure that is most stro ngly coupled\, in a triadic sense\, to small scales\, is the very-large-sc ale-motion (VLSM). The phase of the bispectrum\, the biphase\, shows that there is an interaction delay in the triadic interaction. This will help t o understand the scale interactions better and hopefully shed some light o n the flow control in the turbulent boundary layers. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-232@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210630T163000 DTEND;TZID=Asia/Jerusalem:20210630T173000 DTSTAMP:20230409T143424Z URL:https://aerospace.technion.ac.il/events/an-improved-distributed-consen sus-kalman-filter-design-approach/ SUMMARY:An Improved Distributed Consensus Kalman Filter Design Approach DESCRIPTION:Lecturer:Aviv Priel\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n Sensor networks comprise a group of agents equipped with sen sing devices and communicating capabilities in order to solve the common t ask of cooperative estimation of a detectable physical process. In this fr amework\, each agent in the system activates\, in a distributed fashion\, an estimator\, which relies on local measurements fused with the estimates from other agents in the network.\nA recently developed tool to solve thi s problem is the introduction of a consensus-based term fused with a class ical state estimator structure\, knows as the consensus Kalman filter. In this architecture\, each estimator incorporates a classic Kalman term\, al ong with a consensus term used to fuse the estimates from neighboring agen ts. Our contribution begins with proposing a method based on semi-definite programming to compute a centralized consensus gain term leading to impro ved performance of the estimator over existing solutions.\nWe also propose a decentralized consensus gain that can be computed by each agent and rel ies only on local network properties.\nWe further extend our research to t ackle the important aspects of reducing energy (communication) consumption in network applications. To do so\, we utilize an event triggering mechan ism in which communication is permitted only if certain conditions are met . The main analytical challenge in these  estimator structures is the des ign of the consensus gain term and an event trigger condition that ensures stability while maintaining a prescribed degree of performance. In this d irection\, our contribution continues with proposing both a centralized an d a decentralized consensus gain along with a tailored event triggered con dition. We show that these event trigger estimators out-performs the stand ard non-cooperative local Kalman filter. We provide numerical simulations to demonstrate the effectiveness of our results compared to existing solut ions in the literature. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-60@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210701T183000 DTEND;TZID=Asia/Jerusalem:20210701T183000 DTSTAMP:20221031T074356Z URL:https://aerospace.technion.ac.il/he/events/%d7%9e%d7%a1%d7%99%d7%91%d7 %aa-%d7%a1%d7%99%d7%95%d7%9d-%d7%9e%d7%97%d7%96%d7%95%d7%a8-%d7%a6%d7%90-% d7%a6%d7%91/ SUMMARY:מסיבת סיום מחזור צ"א + צ"ב DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:אמפי טכני ון / בניין הפקולטה\n Zoom: \n Abstract: \n Details: \n מת חילים כללי ב 18:30 באמפי\n19:45 אירוע בפקולטה\n CATEGORIES:אירועים LOCATION:אמפי טכניון / בניין הפקולטה END:VEVENT BEGIN:VEVENT UID:0-237@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210714T133000 DTEND;TZID=Asia/Jerusalem:20210714T143000 DTSTAMP:20230417T065532Z URL:https://aerospace.technion.ac.il/events/oscillations-of-large-bubbles- due-to-sudden-finite-volume-release/ SUMMARY:Oscillations of Large Bubbles Due to Sudden Finite Volume Release DESCRIPTION:Lecturer:Idan Eizenberg\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion .zoom.us/j/99715588822\n Zoom: \n Abstract: \n Details: \n The oscillatory behavior of large air bubbles produced from the instantaneous rupture of a submerged\, finite volume container is characterized experimentally. Con tinuous gas release in the form of a unidirectional jet from underwater pi pes or geophysical formations has received significant attention in the pa st\, largely focused on the break-up of the gas stream and the size of the resulting bubbles. More recently\, so-called ‘glugging’ behavior in c onstrained systems with very large reservoirs has also been studied\, in w hich bi-directional mass exchange occurs between the liquid and gas phases . In contrast to both of these quasi-steady systems\, the finite volume ru pture problem depends significantly on the initial transient behavior of t he two fluids\, due to the bi-directional exchange in a relatively small\, fixed\, gas reservoir. The resulting gas release produces a similar bubbl e break-up behavior but with different time and length scales. We present time-resolved pressure and bubble geometry measurements following an insta ntaneous\, underwater volume rupture\, identify the relevant temporal scal ing behavior for the resulting dynamics\, and explain the behavior in term s of inertial and capillary phenomena. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/99715588822 END:VEVENT BEGIN:VEVENT UID:0-221@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210721T133000 DTEND;TZID=Asia/Jerusalem:20210721T143000 DTSTAMP:20230403T143854Z URL:https://aerospace.technion.ac.il/events/economic-dispatch-for-a-networ k-of-micro-gas-turbines/ SUMMARY:Economic Dispatch for a Network of Micro-Gas Turbines DESCRIPTION:Lecturer:Nati Peleg\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng. + https://technion.zoo m.us/j/92355833611\n Zoom: \n Abstract: \n Details: \n As industry\, busin esses\, and families day to day life rely more and more on new technologie s and electrical appliances\, economic reports present a growth in energy demand. This leads to the need for additional energy suppliers\, which are usually smaller\, spread around (geographically)\, and integrated to the power grid in "smart" manner.  The shift to distributed power generation creates challenges related to their operation.\nWe propose a novel approac h for solving an economic dispatch (ED) problem of a power network compris ed of micro-gas turbines (MGT) together with a utility. The ED problem is naturally formulated as a mixed-integer nonlinear optimization problem whi ch is known to be computationally difficult to solve.  We present a numer ically efficient solution to this problem by decomposing the ED algorithm into two parts. The first part of the decomposition attains an analytic so lution for allocating the output power of each MGT as a function of the to tal requested power. The second part determines the desired total output p ower from the MGTs by modeling all the generators as a single unit.  In t his way\, the problem reduces to a standard ED problem\, and we show how t o solve this efficiently using the celebrated shortest path algorithm.  T his new approach significantly reduces the run-time needed to solve a comp lex optimization problem. We support our results with a numerical study.\n Zoom Meeting CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. + https:// technion.zoom.us/j/92355833611 END:VEVENT BEGIN:VEVENT UID:0-238@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210728T133000 DTEND;TZID=Asia/Jerusalem:20210728T143000 DTSTAMP:20230417T065618Z URL:https://aerospace.technion.ac.il/events/experimental-characterization- and-diagnostic-challenges-of-cathodic-are-jets/ SUMMARY:Experimental Characterization and Diagnostic Challenges of Cathodic Arc Jets DESCRIPTION:Lecturer:Matar Rosen\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zo om.us/j/99050274097\n Zoom: \n Abstract: \n Details: \n Flow control- mani pulation of flow behavior have received significant research attention sin ce the beginning of boundary layer theory\, due to the notable drawbacks o f unplanned flow separation: acoustic noise problems\, drag increase\, lif t losses\, instabilities\, etc.  Flow control methods can be classified b y their technology and their form of flow perturbation. One of these techn ologies is plasma actuation: impulsively perturbing the flow via plasma wi th no moving parts\, low actuator mass and fast time response.\nA cathodic arc is a subset of electric arcs that results in electron emission and va porization of cathode material.  The Cathodic Arc Actuator (CAA) is a dev ice that generates cathodic arc jets. Due to its coaxial structure\, the p articles are accelerated in the direction of the symmetry axis- instead of the direction between electrodes. Although this technology has largely be en utilized for propulsion and material processing\, it can also be applie d to flow actuation and control. For the purpose of flow control the direc tion of the plasma generation creates a unique method of inserting perturb ations perpendicular to the flow.\nIn this study\, the CAA was applied to a canonical separated flow\, the backward facing step. The influence of th e CAA on the flow\, along with detailed processing of the electrical measu rements for the purpose of characterizing the efficiency of the devise wil l be presented. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/99050274097 END:VEVENT BEGIN:VEVENT UID:0-236@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210804T133000 DTEND;TZID=Asia/Jerusalem:20210804T143000 DTSTAMP:20230417T063626Z URL:https://aerospace.technion.ac.il/events/theoretical-study-of-flame-ini tiation-by-electrical-discharge/ SUMMARY:Theoretical study of flame initiation by electrical discharge DESCRIPTION:Lecturer:Nir Druker\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:http s://technion.zoom.us/j/94376262264\n Zoom: \n Abstract: \n Details: \n In Internal Combustion Engines (ICE’s)\, the combustible mixture is ignited at each cycle by a time-controlled spark discharge. The success of the fl ame initiation depends to a large extent on the operating conditions (engi ne speed\, engine load\, ambient conditions\, and spark characteristics). It was found that with traditional ignition systems\, the nature of the ig nition process induces very significant cycle-to-cycle variations\, and as compared to theoretical cycles\, these are believed to be the main reason for lower engine torque\, high fuel consumption and surplus engine emissi on. In order to improve the success level of the ignition process\, quite a number of different ignition systems have been proposed. Higher discharg e energies\, longer discharge durations and multi-spark systems have been developed. During the last decade\, cold-plasma multi-pulse assisted ignit ion systems have been proposed. In practice\, these systems have shown muc h better results\, though our understanding of how the energy evolves in t his complex ignition process is still deficient. Such an understanding is valuable not only for widening and deepening our scientific knowledge\, bu t also to optimize the systems in practical settings.\nIn this research\, we conducted a preliminary\, theoretical/numerical investigation into the possibility of use of on-board control of electrically-based cold plasma-a ssisted ignition and combustion The focus was on diagnostics and enhanceme nt of energy deposition in specific modes\, by application of bi-polar sho rt duration voltage pulses in low-pressure air. The physical model couples the electric field\, potential and current\, with the relevant conservati on equations for 24 species via 168 kinetic reactions\, including molecule s’ rotation\, vibration\, electronic excitation\, dissociation\, and ion ization inside the electrodes gap. Evaluation using various pulse repetiti on frequencies and different pulse shapes was conducted. Special attention was given to the overall coupled energy\, deposited during the discharge\ , and to energy channeled to known ignition supportive modes such as nitro gen electronic excitation and oxygen radicals generation.\nThe results of the analysis show that for the considered conditions\, energy deposition c an be divided into two main stages\, characterized by high and low voltage magnitudes\, respectively. It was found for the first time\, that the (lo w voltage) second stage’s energy deposition can be higher than that of t he first (high voltage) stage. At the second stage\, the deposition of ene rgy into specific modes can be tuned by setting appropriate voltage magnit udes. In addition\, the energy deposited in modes important for ignition\, exhibits a simple linear relation to the overall energy deposition. Furth ermore\, based on these findings\, we demonstrate how a new sequence of vo ltage pulses can further increase enhancement of ignition and combustion s upportive processes.\nlink to Zoom CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/94376262264 END:VEVENT BEGIN:VEVENT UID:0-217@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210818T133000 DTEND;TZID=Asia/Jerusalem:20210818T143000 DTSTAMP:20230403T122844Z URL:https://aerospace.technion.ac.il/events/synthesis-of-linear-robust-con trollers-for-flutter-suppression-with-performance-and-uncertainty-specific ations-tuned-by-genetic-algorithms/ SUMMARY:Synthesis of Linear Robust Controllers for Flutter Suppression with Performance and Uncertainty Specifications Tuned by Genetic Algorithms DESCRIPTION:Lecturer:Noam Yechiely\n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion. zoom.us/j/95436734611\n Zoom: \n Abstract: \n Details: \n Aircraft structu res\, specifically wings\, are inherently flexible\, resulting in aeroelas tic interactions between the deformed configuration and the aerodynamic fo rces acting on it. One such aeroelastic interaction is flutter - a self-su stained oscillation phenomenon that often leads to structural failure. Sin ce flutter might be destructive\, it is commonly avoided by restricting th e flight envelope to flutter-free regions. Flutter in the flight envelope can be avoided by using Active Flutter Suppression (AFS) technologies that push the flutter onset to higher dynamic pressure values. Several recent studies investigated the use of linear control design methods in AFS syste ms\, where the design method for the controller includes optimal and robus t control techniques. The major drawback of those methods is that they are limited to linear design models and requirements.\nThe current study focu ses on developing a method for linear controller synthesis that accounts f or nonlinear design specifications. This is done using external nonlinear optimization that modifies the synthesis set-up to achieve improved (nonli near) performance and selection of an optimal controller via Genetic Algor ithm (GA) optimization. The method is demonstrated on the Active Aeroelast ic Aircraft Testbed (A3TB)\, a flying-wing UAV platform that experienced f lutter in flight. The seminar will present the aeroelastic modelling of th e aircraft\, aeroservoelastic analyses\, nominal AFS controller design\, a nd GA-based controller tuning. The optimization was successfully performed \, increasing the flutter speed onset of the closed-loop system from 29 to 61 m/s\, which is outside the flight envelope. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/95436734611 END:VEVENT BEGIN:VEVENT UID:0-228@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210823T133000 DTEND;TZID=Asia/Jerusalem:20210823T143000 DTSTAMP:20230409T142806Z URL:https://aerospace.technion.ac.il/events/intelligent-lightweight-aerosp ace-structures/ SUMMARY:Intelligent Lightweight Aerospace Structures DESCRIPTION:Lecturer:Professor Michele Meo\n Faculty:Department of Mechanic al Engineering\n Institute:University of Bath\n Location:https://technion. zoom.us/j/98188055502\n Zoom: \n Abstract: \n Details: \n A major ambition of aerospace industries is to improve flight performance of commercial an d military aircraft. One of the key activities towards this ambition is t he development of high performance structural composite materials. Compos ite materials are specifically of interest to aerospace applications b ecause of their low weight and increase strength. The development and de ployment of new structural composite technologies will have the greates t impact on the reduction of weight and operational costs of aircraft com pared with other technologies. The vulnerability however of composite structures to localised\, dynamic\, sudden\, unexpected and impact loads \, such as foreign object damage\, may result in unpredictable complex lo calized damage and a loss of post-impact residual strength.\nIn order to  efficiently exploit composite materials\, there is a stringent need to develop means to detect dynamic loadings  alongside improvement in sm art sensing\, inspection and maintenance techniques in a timely and cost efficient manner. This talk discuss novel Structural Health Monitoring a nd Non-Destructive techniques based on non-linear acoustics methods\, Smar t Materials (Shape memory alloys and graphene) and Structures\, and materi al models and simulation methods for the design and manufacture intellige nt aerospace composite structures under  impact loadings that could lead to a significant reduction of weight\, design and certification cost.\nh ttps://technion.zoom.us/j/98188055502\n\n \; CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/98188055502 END:VEVENT BEGIN:VEVENT UID:0-220@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20210929T133000 DTEND;TZID=Asia/Jerusalem:20210929T143000 DTSTAMP:20230403T143650Z URL:https://aerospace.technion.ac.il/events/hydrodynamic-stability-of-mult i-phase-shear-flows-laden-with-interacting-particles/ SUMMARY:Hydrodynamic stability of multiphase shear flows laden with interac ting particles DESCRIPTION:Lecturer:Zhixuan Liu\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zo om.com.cn/j/7152833139\n Zoom: \n Abstract: \n Details: \n Multiphase flow s laden with interacting polydisperse particles are frequently encountered in aerospace propulsion\, atmospheric flows\, as well as in environmental and medical applications. The stability characteristics of such flows can experience drastic changes compared to their clean state due to inter-pha se and inter-particle heat and mass transfer. Disperse particulate matter has been found to alter the onset of laminar to turbulent transition and l ead to modulation of turbulence in multiphase flows. Saffman (1962) conduc ted the first linear stability analysis of particle-laden shear flows and proposed that the addition of fine dust either stabilizes or destabilizes the carrier gas flow depending on the particles’ relaxation time scales relative to the carrier flow time scale. Numerical simulations of multipha se flows that involve tracking each interacting particle in a Lagrangian f ramework require extreme computational resources and are thus limited for the study of stability. The complexity of such flows is further increased when interactions such as droplet evaporation\, coalescence\, breakup\, et c.\, are considered.\nTo extend current hydrodynamic stability theories in multiphase flows and analytically resolve interacting polydisperse partic les\, we revisit Saffman’s theory for dusty gas flows and develop a new generalized mathematical framework by combining a linear stability analysi s and a discrete Eulerian formulation for the flow and dispersed matter. I n this talk\, we will introduce the generalized mathematical framework and present the stability characteristics of multiphase flows involving diffe rent shear flow configurations: Polydisperse Channel flows and Polydispers e evaporating pipe flows at low and high Reynolds numbers and various part iculate matter loadings.  Finally\, we discuss the specific mechanisms re sponsible for the onset of instability in each particle-laden flow case.\n link to Zoom CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.com.cn/j/7152833139 END:VEVENT BEGIN:VEVENT UID:0-222@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20211013T133000 DTEND;TZID=Asia/Jerusalem:20211013T143000 DTSTAMP:20230403T144025Z URL:https://aerospace.technion.ac.il/events/turbulent-coherent-structures- and-particle-clusters-in-a-high-reynolds-number-water-tunnel/ SUMMARY:Turbulent Coherent Structures and Particle Clusters in a High Reyno lds Number Water Tunnel DESCRIPTION:Lecturer:Guangyao Cui\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.z oom.us/j/94669656281\n Zoom: \n Abstract: \n Details: \n Turbulent flows a re composed of a wide range of large- and small-scale coherent motions in both the momentum field and the particle field. These motions are responsi ble for practical engineering effects\, like the generation of turbulent d rag and particle mixing. Scale interactions between large- and small-scale s in turbulent wall-bounded flows have historically been investigated by l inear analysis which requires a filtering and envelope procedure. The phas e delay between large and small scales was explained as a spatial delay in the flow. However\, this linear analysis depends on the cutoff wavelength in the filtering process and the use of an artificial envelope of small s cales that does not exist in real data. A nonlinear diagnostic\, the bispe ctrum\, is introduced and applied to a numerical turbulent channel flow. T he bispectrum shows that large-scale structure that is most strongly coupl ed\, in a triadic sense\, to small scales\, is the very-large-scale-motion (VLSM). The large scale structures can not only be detected in the moment um field\, but also in the particle field. The wavelet transform was appli ed to extract the statistically significant\, spatial particle clusters. I nertial particles were seeded in the high speed water tunnel facility\, an d two-color PIV/PTV measurement was performed to investigate the coherent motions in both the momentum and particle field.\nZoom Meeting\n\n \; CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/94669656281 END:VEVENT BEGIN:VEVENT UID:0-218@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20211020T133000 DTEND;TZID=Asia/Jerusalem:20211020T143000 DTSTAMP:20230403T143501Z URL:https://aerospace.technion.ac.il/events/an-experimental-aeroelastic-be nchmark-of-a-very-flexible-wing/ SUMMARY:An Experimental Aeroelastic Benchmark of a Very Flexible Wing DESCRIPTION:Lecturer:Or Avin\n Faculty:Design and Manufacturing Management\ n Institute:Technion – Israel Institute of Technology\n Location:Classro om 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zoom.u s/j/95043873801\n Zoom: \n Abstract: \n Details: \n The progress towards l ighter and more efficient aircraft structures has led to some very flexibl e wing configurations that deform to a great extent under flight loads. Su ch designs experience unique aeroelastic phenomena that the industry-stand ard linear structural and aeroelastic models might not accurately predict. In recent years\, there has been an ongoing effort in the aeroelasticity community to develop novel nonlinear models in both the structure and aero dynamic disciplines to analyze very flexible configurations. These models require validation\, which calls for aeroelastic wind tunnel or flight tes ts. Aeroelastic wind tunnel tests can be used to assess the accuracy and v alidity of computational models and point to new physics.\nThe seminar wil l present the design\, analyses\, and wind-tunnel testing of the Pazy wing -  a very flexible wing model designed to study nonlinear aeroelastic ph enomena due to geometrically large deflections. Wind tunnel tests were con ducted at the Faculty of Aerospace Engineering subsonic wind tunnel in con ditions that lead to static and dynamic\, stable and unstable\, responses. At extreme conditions\, static deformations of 50% span were recorded\, a s well as instances of limit-cycle oscillations. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/95043873801 END:VEVENT BEGIN:VEVENT UID:0-226@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20211027T183000 DTEND;TZID=Asia/Jerusalem:20211027T193000 DTSTAMP:20230409T141725Z URL:https://aerospace.technion.ac.il/events/experimental-investigation-of- circular-scramjets-in-high-enthalpy-flows-from-flow-choking-to-inlet-buzz/ SUMMARY:Experimental Investigation of Circular Scramjets in High Enthalpy F lows: From Flow Choking to Inlet Buzz DESCRIPTION:Lecturer:Qili Liu\n Faculty:School of Aeronautics and Astronaut ics\n Institute:Purdue University\n Location:https://purdue-edu.zoom.us/j/ 7448516056\n Zoom: \n Abstract: \n Details: \n Unsteady fluid-combustion i nteractions in optical axisymmetric scramjet models are experimentally inv estigated in Mach 4.5 flows. The axisymmetric scramjet reveals generic flu id and combustion dynamics without the corner boundary-layer effects that can distort flame propagation in rectangular geometries. Fluid and combust ion dynamics are characterized by pressure measurement on the combustor wa ll along the entire flowpath. High-speed flame chemiluminescence and lumin osity imaging are used to visualize the unsteady shock and flame propagati ons driven by fluid-combustion interactions. It is shown that the initial choking location of the scramjet combustors depends on the competing effec t of combustion heat addition and combustor area relief. For the 2° combu stor\, the combustion-induced flow choking occurs inside the diverging sec tion of the combustor\, while the 5° combustor cannot be thermally choked due to the excessive area expansion. The unsteady pseudo shock propagates upstream until it reaches the cavity flameholder. A shock train is establ ished in the isolator to balance the pressure rise downstream. Once the sh ock train is disgorged out of the inlet\, a normal shock is formed in fron t of the inlet\, i.e.\, inlet unstart. Inlet buzz phenomenon is observed a t unstarted conditions due to the fluid-combustion interaction. The buzz f requency is correlated to the acoustic wave propagation in the subsonic fl ow regime established between the inlet and the flow choked location. Neve rtheless\, the resonance mode for a duct with an open and a closed-end is applicable only to the case with an initial choking location at the cavity ramp.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://purdue-edu.zoom.us/j/7448516056 END:VEVENT BEGIN:VEVENT UID:0-227@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20211108T163000 DTEND;TZID=Asia/Jerusalem:20211108T173000 DTSTAMP:20230409T142716Z URL:https://aerospace.technion.ac.il/events/stochastic-interception-using- particle-filtering-and-smoothing-and-a-time-varying-delayed-information-ga me/ SUMMARY:Stochastic Interception Using Particle Filtering and Smoothing\, an d A Time-Varying Delayed-Information Game DESCRIPTION:Lecturer:Liraz Mudrik\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.z oom.us/j/99045396257\n Zoom: \n Abstract: \n Details: \n In a real-world\, stochastic pursuit-evasion game\, a sudden change in the target's evasion maneuver generates an inevitable time delay at the pursuer's estimator\, due to its inherent reliance on incomplete and noisy measurements. In turn \, this time delay might severely degrade the pursuer's worst-case interce ption performance. A common approach to address this challenge is to incor porate time delay(s) in the deterministic derivation of the guidance law. However\, these solutions unrealistically assume that the delay is constan t throughout the game\, and\, because the value of the delay is unknown\, it is generally regarded as a tuning parameter only. Moreover\, these solu tions feed the delayed-information guidance law with current (filtered) ti me estimates\, thus breaking the assumptions underlying the derivation of this law.\nWe present a novel tracking and interception strategy that addr esses the aforementioned problems in a game involving highly maneuverable targets. We first solve a bounded-control differential game with two time- varying delays\, thus extending an already known result. Second\, we intro duce a novel algorithm for online estimation of these delays using semi-Ma rkov chains\, without requiring the standard assumptions of linearity and Gaussian distributions. Finally\, as the developed guidance law requires d elayed information about two states\, we use a fixed-lag particle smoother to provide the best information at the appropriate time.  This approach renders an improved framework for intercepting an evasively maneuvering ta rget in a stochastic setting\, where a sophisticated target can exploit th e inherent estimation delay for evasion.  We evaluate the performance of this methodology using a thorough Monte-Carlo simulation study.\nZoom Meet ing CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/99045396257 END:VEVENT BEGIN:VEVENT UID:0-239@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20211115T170000 DTEND;TZID=Asia/Jerusalem:20211115T180000 DTSTAMP:20230417T065821Z URL:https://aerospace.technion.ac.il/events/study-of-the-deflagration-regi me-along-the-hugoniot-curve/ SUMMARY:Study of the deflagration regime along the Hugoniot curve DESCRIPTION:Lecturer:Dina Loktev\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:htt ps://technion.zoom.us/j/93264073949\n Zoom: \n Abstract: \n Details: \n A physical approach of calculating the laminar flame speed in homogeneous me dium takes into consideration the preservation of Mass\, Energy and Moment um\, and using the Ideal Gases relations - yields a system of 4 equations with 5 unknowns\, which can be simplified into the graphic intersection of Rankine Lines (denoted from the Rayleigh equation) and the Hugoniot Curve . Chapman-Jouguet suggested that the tangent points will determine the fla me speed in both regimes\, and while this thesis correctly estimates the D etonation speed\, the Deflagration velocity predicted is 2 magnitudes of o rder higher than expected. A lot of different approaches were suggested ov er the years to correctly forecast the Deflagration velocity\, the leading one (up until today) is the Thermal Theory that predicts a good approxima tion of the laminar speed but does not conform to the Momentum equation.\n Lately\, a new approach relying on thermodynamic stability\, transition ph enomena (mass and heat) and the principal of Entropy increase has been sug gested. The work was based on introduction of the principals of irreversib le thermodynamics\, as formulated by Lars Onsager in the 1930s\, into the Thermal Theory. Validations for Methane-Air lean mixtures showed good resu lts.\nThe present study is the first one to apply the new theory and keeps developing it. The main achievements:\n\n\n cancelation of calibration p arameters\n Full calculation of the flame front width (using one-step mod els for the Reaction Rates)\n First application in analytical theories – temperature dependant model for thermodynamic characteristics\n Compl etion of proof for the Applicability of the new theory\n\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/93264073949 END:VEVENT BEGIN:VEVENT UID:0-216@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20211124T133000 DTEND;TZID=Asia/Jerusalem:20211124T143000 DTSTAMP:20230403T122604Z URL:https://aerospace.technion.ac.il/events/active-noise-cancellation-via- thermo-acoustic-transducers/ SUMMARY:Active Noise Cancellation via Thermo-Acoustic Transducers DESCRIPTION:Lecturer:Boris Leizeronok\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https://techni on.zoom.us/j/95067058771\n Zoom: \n Abstract: \n Details: \n Sound product ion via Joule heating has been observed since late 19th century. The term “thermophone” was coined soon after to define an acoustic transmitter\ , where an alternating electrical current produces surface heat-flux fluct uations and\, consequently\, pressure waves in the surrounding fluid. Such transducers offer several potential advantages over conventional mechanic al devices owing to their design simplicity\, lightweight structure and ac oustic purity. Moreover\, thermophones are a promising technological step in the field of active noise cancellation. The ability to generate sound w ithout mechanical motion enables to place the emitter directly at the nois e source rather than at the remote point of observation\, resulting in a g lobal destructive interference. Recent theoretical papers predict that for the case of vibrating noise boundary (such as conventional loudspeaker)\, at the optimal cancellation point\, the ratio between the thermal and kin etic energies of the two co-planar sources depends on the heat capacity ra tio of the fluid medium that surrounds the acoustic system.\nAlthough elec tro-thermo-acoustic energy conversion process has been the centerpiece of several studies\, there is no clear consensus as to the correct approach t o modelling thermophone sound production. This leads to a lack of understa nding which structural properties would result in an optimal thermo-acoust ic transducer. The present research addresses this gap by implementing sta te-of-the-art thermophone simulation framework\, coupled with extensive ex perimental campaign\, that provide an outlook on the performance impact as sociated with various thermophone geometrical and physical properties. In following\, feasibility of active noise cancellation of a vibrating source is demonstrated in various gaseous media.\nZoom meeting CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/95067058771 END:VEVENT BEGIN:VEVENT UID:0-219@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20211213T133000 DTEND;TZID=Asia/Jerusalem:20211213T143000 DTSTAMP:20230403T143547Z URL:https://aerospace.technion.ac.il/events/modelling-and-design-of-geared -mechanical-powertrains-for-aerospace-questions-of-architecture-simplicity -versus-complexity-and-future-outlook/ SUMMARY:Modelling and design of geared mechanical powertrains for aerospace - questions of architecture\, simplicity versus complexity\, and future o utlook DESCRIPTION:Lecturer:Christos Spitas\n Faculty:Machine Design\n Institute:N azarbayev University\n Location:\n Zoom: \n Abstract: \n Details: \n We an alyse some of the main challenges in the geared mechanical transmissions o f modern aeroengines such as large-bypass-ratio turbofans\, open rotors a nd turboshafts/ turboprops in terms of efficiency\, power density\, weigh t\, and reliability down to their casualties and present related models f rom recent research. We demonstrate limits to the existing architectures a nd\, following basic principles of mechanics\, we discuss how different to pologies and interface geometries may help affect force- and torque-transf er to produce better efficiency\, material utilisation\, power density and light weight\, insensitivity to errors and perturbations\, including fail -safety\, and ultimately higher reliability and lower cost. Beyond its str ict disciplinary focus\, we use the presented case to raise questions rega rding how to approach design effectively at the level of architecture and how to reconcile simplicity\, where one may hope to find design intent\, w ith complexity and the realm of "the details"\, where the devil proverbial ly resides.\n CATEGORIES:Seminars END:VEVENT BEGIN:VEVENT UID:0-224@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220103T143000 DTEND;TZID=Asia/Jerusalem:20220103T153000 DTSTAMP:20230409T103254Z URL:https://aerospace.technion.ac.il/events/compressible-flow-investigatio ns-at-tri-sonic-speeds-a-research-summary-of-a-few-selected-experiments/ SUMMARY:Compressible flow investigations at tri-sonic speeds: a research su mmary of a few selected experiments DESCRIPTION:Lecturer:SK Krathick\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zo om.us/j/94882385466\n Zoom: \n Abstract: \n Details: \n Investigations of internal and external flow at high speeds have paramount importance in arr iving at a sustainable propulsion and effective aerodynamics for supersoni c/hypersonic transit. Mixing gaseous fuel and air mixture at a higher velo city is difficult to predict and model\, owing to the complicated non-line ar process involved in scalar mixing. Similarly\, fluctuations propagating upstream due to combustor back pressure variations in a hypersonic inlet could be violent and render the shock systems to remain in a self-sustaine d oscillating state under certain operating conditions. In the present tal k\, representative cases of internal and external flows at tri-sonic speed s from my research activities will be summarized. Firstly\, findings of mi xing length in a supersonic confined jet will be examined through differen t experiments. The tonal noise suppression using rear face modifications i n the transonic cavity flow will be further discussed through both experim ents and computations. Later\, shock-related unsteadiness arising from the leading-edge separation in external flows at both supersonic and hyperson ic Mach numbers will be elaborated through experimental and computational findings. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/94882385466 END:VEVENT BEGIN:VEVENT UID:0-229@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220105T133000 DTEND;TZID=Asia/Jerusalem:20220105T143000 DTSTAMP:20230409T142932Z URL:https://aerospace.technion.ac.il/events/hybrid-approach-to-predict-and -optimize-flaw-detection-capabilities-using-laser-shearography/ SUMMARY:Hybrid Approach to Predict and Optimize Flaw Detection Capabilities using Laser Shearography DESCRIPTION:Lecturer:Yair Elbaz\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zoo m.us/j/91091112215\n Zoom: \n Abstract: \n Details: \n In recent years\, t here is significant integration of composite elements in the aviation worl d due to their unique benefits. However\, these elements also have disadva ntages – the sensitivity to production process and limitations of\nnon-d estructive testing (NDT) methods. NDT of composite structures is a global challenge. One of the main methods\, which has been gaining momentum in re cent years\, is the Laser Shearography Testing (LST). Today\, due to depen dence on several parameters\, LST detection capabilities for composite str uctures\, are not known in advance. The manner in which the NDT procedures are currently being developed is based on accumulated experience\, trial and error\, and a number of "rules of thumb". In the present study\, we pr esent a theoretical\, analytical and experimental study of the engineering prediction of shearography fringe pattern. We had developed a methodology which was implemented as a simulation that can evaluate the LST fringe pa ttern in advance. The simulation was tested by comparing its results to re presentative cases from the literature and by conducting a practical exper iment by LST system yielding a good match. Subsequently\, "Detection Capab ility Envelopes" were constructed for the LST which makes it possible to a ssess the flaws detection capability in advance depending on a variety of parameters. These\, can be used as a guide and as a reference point for al l those involved in the testing process using the LST method\, developers and technicians alike\, for the more efficient and accurate flaws detectio n in aviation structures – which will lead to improved  flight safety.\ nZoom Meeting CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/91091112215 END:VEVENT BEGIN:VEVENT UID:0-214@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220110T133000 DTEND;TZID=Asia/Jerusalem:20220110T143000 DTSTAMP:20230403T122400Z URL:https://aerospace.technion.ac.il/events/cavitation-and-bubble-dynamics -in-aviation-fuels/ SUMMARY:Cavitation and bubble dynamics in aviation fuels DESCRIPTION:Lecturer:Dr. Igal Gluzman\n Faculty:Department of Aerospace and Mechanical Engineering\n Institute:University of Notre Dame\, Indiana\, U SA\n Location:https://notredame.zoom.us/j/7498300665?pwd=ck5lM1JPbzE5dXRCa DdCQ3VjOGw4dz09\n Zoom: \n Abstract: \n Details: \n Cavitation in the airc raft fuel systems can lead to unexpected damage to fuel-system components. Modeling fuel cavitation is challenging due\, in part\, to the fact that fuels are a complex mixture of hundreds of hydrocarbons. This study is foc used on the fundamental understanding of cavitation inception\, shock wave generation mechanisms\, and bubble dynamics in aviation fuels via rigorou s experimental studies and modeling efforts.\nFirst\, we present unprecede nted quantitative data on shock wave propagation characteristics in the co nverging-diverging nozzle obtained via a novel high-speed image processing technique we term "enhanced gradient shadowgraphy". Two sustained mechani sms are found to be responsible for shock wave generation. We obtain nonli near solutions of the governing equations to predict shock speeds. Good ag reement is achieved with experimental data.\nSecond\, we employ advanced c omputer-vision algorithms to extract quantitative data from high-speed ima ging on the bubble spatial-temporal evolution and breakup kinematics. We s how that the initial bubble size plays an essential role in the resulting void fraction variation but not in the breakup kinematics. We also define a unique dimensionless parameter that predicts the bubble breakup event fo r different fuels and flow regimes.\nLastly\, we derive a new model to pre dict cavitation collapse in radial flow between two parallel disks with a thin gap\, representing a geometry relevant to aviation fuel pumps. The mo del predictions of the cavitation cloud collapse in the disk geometry show remarkable agreement with experimental data. Our findings shed light on t he complex physics of fuel cavitation and the dynamics of nonspherical cav ities.\nZoom meeting CATEGORIES:Seminars LOCATION:https://notredame.zoom.us/j/7498300665?pwd=ck5lM1JPbzE5dXRCaDdCQ3V jOGw4dz09 END:VEVENT BEGIN:VEVENT UID:0-225@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220112T133000 DTEND;TZID=Asia/Jerusalem:20220112T143000 DTSTAMP:20230409T141227Z URL:https://aerospace.technion.ac.il/events/the-product-form-of-projection -based-reduced-order-models-and-its-application-to-model-reduction-for-mul ti-agent-systems/ SUMMARY:The Product Form of Projection-Based Reduced Order Models and Its A pplication to Model Reduction for Multi-Agent Systems DESCRIPTION:Lecturer:Noam Leiter\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zo om.us/j/96270648292\n Zoom: \n Abstract: \n Details: \n Model-order reduct ion is an essential tool for large-scale systems introduced by modern tech nologies for which full order controller design and implementation may be numerically and computationally infeasible. Model order reduction is a wel l established field of research in control and systems theory. Of particul ar interest in recent years is the study of model reduction for multi-agen t systems which are characterized by their increasingly large scales.\nIn this talk\,  we reexamine the well known orthogonal projection-based redu ced-order models (PROMs) and their realizations. A novel product form is d erived for the reduction error system of these reduced models\, and invest igating the error system product form\, we then define interface-invariant PROMs\, model order reductions with projection-invariant input and output matrices. It is shown that for such PROMs the error product systems are s trictly proper. Furthermore\, exploiting this structure\, an analytic H∞ reduction error bound is obtained and an H∞ bound optimization problem is defined. We then leverage these results for model reduction of large-sc ale multi-agent systems.  We show how graph contractions can be used to o btain structure-preserving PROMs\, and present a sub-optimal  H∞ graph- based efficient algorithm for model reduction of multi-agent systems. We t hen demonstrate these results on the classical controlled consensus model. \nZoom Meeting CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/96270648292 END:VEVENT BEGIN:VEVENT UID:0-230@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220126T163000 DTEND;TZID=Asia/Jerusalem:20220126T173000 DTSTAMP:20230409T143011Z URL:https://aerospace.technion.ac.il/events/gnc-algorithm-development-for- a-low-cost-research-missile/ SUMMARY:GNC Algorithm Development for a Low-Cost Research Missile DESCRIPTION:Lecturer:Anne Kitzmiller\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :https://technion.zoom.us/j/97696029786\n Zoom: \n Abstract: \n Details: \ n In this talk the flight software containing the GNC algorithms for a low -cost research missile will be presented. The research missile will be emp loyed as a recoverable testbed for the integration and evaluation of advan ced flight algorithms. This reusability is intended to reduce the cost of flight test\, and the overall cost of each test asset is contained by util izing commercial off-the-shelf avionics in the missile. An effective missi le test platform is both reliable and recoverable\, such that it can be re used for subsequent flight testing. The missile configuration and proposed GNC algorithms were designed to achieve these objectives. The flight soft ware is comprised of four modules: guidance\, navigation\, control\, and f light logic. The proposed control architecture is that of a skid-to-turn m issile\, such that the missile tracks vertical and horizontal acceleration commands Az and Ay while regulating the roll angle phi to zero. The guida nce algorithm generates the Az\, Ay and phi commands for executing desired trajectory. The flight logic defines the phases of flight along the traje ctory and contains algorithms for detecting the transition events includin g launch\, main engine cutoff\, apogee\, and recovery. The flight software and missile performance are evaluated using 6DOF simulations and Monte Ca rlo analyses. The code is then compiled and implemented on the Pixhawk fli ght computer and tested by Processor-in-the-Loop and Hardware-in-the-Loop simulations. CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/97696029786 END:VEVENT BEGIN:VEVENT UID:0-215@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220207T163000 DTEND;TZID=Asia/Jerusalem:20220207T173000 DTSTAMP:20230403T122448Z URL:https://aerospace.technion.ac.il/events/generation-of-skeletal-chemica l-mechanisms-of-liquid-hydrocarbon-fuels-for-cfd-applications/ SUMMARY:Generation of Skeletal Chemical Mechanisms of Liquid Hydrocarbon Fu els for CFD Applications DESCRIPTION:Lecturer:Alon Naor\n Faculty:Department of Aerospace Engineerin g\n Institute:Technion – Israel Institute of Technology\n Location:https ://technion.zoom.us/j/99956478137\n Zoom: \n Abstract: \n Details: \n This work suggests and demonstrates a method for generating reduced chemical k inetic mechanisms for aviation fuels. Small but accurate mechanisms are ne eded for use in Computational Fluid Dynamics (CFD) combustion applications \, saving complex and expensive lab experiments. The focus is on the abili ty to predict flame stabilization in premixed pre-vaporized gas turbine co mbustors on elevated pressures and high temperature conditions\, which des cribe practical combustion. Initially\, the Reaction Mechanism Generator i s used for generating a detailed mechanism at compositions and conditions of interest\, for which experimental data may be limited or nonexistent. S ubsequently\, a path flux analysis algorithm is used to generate reduced m echanisms with different numbers of species.  Finally\, laminar premixed flame\, opposed jet premixed flame\, and auto-ignition calculations are us ed to select the smallest mechanism with an acceptable error. The method w as implemented to generate reduced mechanisms of key fuel components - pro pane\, n-dodecane\, methyl-cyclo-hexane\, and surrogate of JP-8 aviation f uel at an elevated pressure of 20 atm. The work includes validations with the limited available experimental data and sensitivity analyses. The redu ced mechanisms presented satisfactory performances compared to existing on es\, despite their much smaller size. With the suggested process\, one can generate new skeletal chemical mechanisms which predict quite well the co mbustion phenomena of interest at the actual combustor conditions. This is especially useful when relevant experimental data is not available for mo del optimization. The new approach can be used to improve the representati on of the chemical kinetic process of real jet fuels in CFD simulations.\n Zoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/99956478137 END:VEVENT BEGIN:VEVENT UID:0-186@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220209T013000 DTEND;TZID=Asia/Jerusalem:20220209T023000 DTSTAMP:20230108T145338Z URL:https://aerospace.technion.ac.il/events/high-speed-hot-wire-anemometry -towards-independent-characterization-of-instantaneous-flow-quantities-wit h-minimal-calibration/ SUMMARY:High-speed Hot-Wire anemometry towards independent characterization of instantaneous flow quantities with minimal calibration DESCRIPTION:Lecturer:Yonit Goren Zaslavsky\n Faculty:Department of Aerospac e Engineering\n Institute:Technion – Israel Institute of Technology\n Lo cation:https://technion.zoom.us/j/91960400649\n Zoom: \n Abstract: \n Deta ils: \n Hot Wire Anemometry (HWA) methodology has yet to fully realize its potential. As a consequence\, nowadays\, the use of HWA is unapplicable t o flow conditions in the range of 0.4<\;M<\;1.2. This research aims to address this gap by extending the use of HWA to cover the compressible fl ow range typical in turbomachinery applications.\nThis research proposes a novel method to decouple and obtain the instantaneous characteristics of the flow\, for an incompressible and supersonic field using HWA probe with at least 3 wires. The sensitivities of the velocity\, Temperature and den sity\, to the electrical voltage applied on the wire  \, are obtained fro m normalized characteristics of the flow ( \,  and ). Using a calibration process Reynolds-Nusselt curve is generated. This calibration can be cond ucted in a free jet facility without the need of a complex closed loop win d tunnel. Using a probe with slanted wires\, a decouple of the flow angles can be obtained\, by calibrating the ratio between the free stream Reynol ds and the effective Reynolds on the wire to the flow angle.\n5 Wire HWA w as created to demonstrate the capabilities of the probe towards conducting an experiment on an engine. Optimization was used to set the best wire pr operties such as wire temperature and diameter to maximize the accuracy of the results.\nA probe calibrated in this manner can therefore provide acc urate instantaneous data of small fluctuations in the flow and can potenti ally lead to a breakthrough in the research and development of state-of-th e-art turbomachinery applications. CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91960400649 END:VEVENT BEGIN:VEVENT UID:0-210@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220214T133000 DTEND;TZID=Asia/Jerusalem:20220214T143000 DTSTAMP:20230403T122011Z URL:https://aerospace.technion.ac.il/events/the-dynamics-and-diffusion-of- brownian-particles-in-unsteady-flows/ SUMMARY:The dynamics and diffusion of Brownian particles in unsteady flows DESCRIPTION:Lecturer:Nan Wang\n Faculty:Applied Mathematics\n Institute:Tec hnion – Israel Institute of Technology\n Location:https://technion.zoom. us/j/98061754875?pwd=WVV1NTlrYlRTamlqelB3VENBdDhsQT09\n Zoom: \n Abstract: \n Details: \n Brownian motion\, the random motion of particles suspended in a medium\, was first studied mathematically by Einstein and Smoluchows ki. They obtained the particle's mean square displacement (MSD) in a quies cent medium. Compared to the classical Brownian diffusion described by the Einstein-Smoluchowski equation\, where the MSD is proportional to time\, the anomalous Brownian diffusion\, where the MSD has a non-linear function of time\, is studied based on the Langevin equations. Contrary to previou s studies in this field\, we investigate Brownian diffusion using stochast ic calculus instead of classical calculus.\nFirst\, we investigate the sto chastic dynamics of free Brownian particles in a sinusoidal wave flow. It indicates that flows in which the velocity depends only on time will not a ffect the particle’s diffusion. Then\, the stochastic dynamics of free B rownian particles in two-dimensional laminar flows in which the velocity p rofiles are polynomial functions of the transverse coordinate are studied. Our new method is validated for two different flow cases without boundary effects: Couette flow and Plane Poiseuille flow. We show that for time sc ales much smaller than the particle relaxation time scales\, the particle almost travels at its initial velocity and that the Brownian diffusion is virtually the same as in quiescent or uniform fluids. On the other hand\, to leading order and for long time scales\, the time dependency of the var iance is . This is due to Brownian diffusion affected by the flow's veloci ty gradients\, where the particle may be carried by the flow to a wide ran ge in the streamwise direction. It reveals that Brownian motion in transve rse directions and the velocity profile of the flow make a significant dif ference to the particle's diffusion in the streamwise direction.\nFinally\ , we explore the response of Brownian particles to a flow propagating by a horizontally oscillating plate. We found an analytical solution for the p article dynamics. A new exact solution is provided for the cases in which Brownian motion is negligible. We show that the diffusion in the horizonta l direction is greatly affected by Brownian motion in the vertical directi on and the function of the flow's velocity\, which also verifies our study on Brownian diffusion of the polynomial case.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/98061754875?pwd=WVV1NTlrYlRTamlqelB3VEN BdDhsQT09 END:VEVENT BEGIN:VEVENT UID:0-211@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220216T133000 DTEND;TZID=Asia/Jerusalem:20220216T143000 DTSTAMP:20230403T122059Z URL:https://aerospace.technion.ac.il/events/a-data-driven-approach-to-deve loping-an-aeroelastic-flutter-precursor/ SUMMARY:A Data-Driven Approach to Developing an Aeroelastic Flutter Precurs or DESCRIPTION:Lecturer:Boaz Meivar\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:htt ps://technion.zoom.us/j/91941118270\n Zoom: \n Abstract: \n Details: \n Th is talk will present a novel algorithm for early detection of aeroelastic flutter when onset conditions are approached during flutter tests of fligh t vehicles. The approached stability boundary is detected by identifying s ubstantial regularity increase of the structural vibrations.  Two new reg ularity features are presented and examined along with existing regularity features used in previous work. The flutter early warning is accomplished using measured signals only\, in response to clear-air turbulence\, and w ith essentially no prior knowledge needed about the aircraft or the flutte r mechanism involved. The algorithm consists of three stages: (1) extracti on of regularity features\, (2) calibration by addition of white noise to nominal measurements\, and (3) thresholding. Four types of datasets were u sed: (a) synthetic data\, (b) simulated data generated using aeroelastic r esponse simulations to stochastic gusts\, (c) measured data from a flutter wind tunnel experiment\, and (d) data recorded in a previously performed flight test with several non-distructive flutter events. Feature selection and evaluation was performed on synthetic data and validated on measured signals. Threshold values were obtained from wind tunnel data and were sho wn to be applicable for flight test data. The algorithm was shown to be ab le to flag an impending flutter event before critical onset occurs for the A3TB UAV flight test sensor measurements.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/91941118270 END:VEVENT BEGIN:VEVENT UID:0-188@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220221T013000 DTEND;TZID=Asia/Jerusalem:20220221T023000 DTSTAMP:20230108T145744Z URL:https://aerospace.technion.ac.il/events/scalar-mixing-and-turbulent-st ructure-measurements-in-a-model-combustor/ SUMMARY:Scalar Mixing and Turbulent Structure Measurements in a Model Combu stor DESCRIPTION:Lecturer:Burak Gokoz\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:htt ps://technion.zoom.us/j/95930528324\n Zoom: \n Abstract: \n Details: \n Ex perimental measurements in actual combustors typically produce measurement s that are narrowly relevant to only specific geometries and not easily ge neralized. Moreover\, in experimental studies\, relevant mixing scales (e. g.\, Batchelor scales) are difficult to observe due to the resolution limi tations of the imaging sensors. As a result\, critical mixing features are not captured\, preventing a reasonable comparison with numerical results. In this project\, we aimed to overcome these challenges by experimentally resolving the mixing scales relevant to turbulent combustion by using a s implified and abstracted model combustion chamber.\nWe devised an experime ntal arrangement to simultaneously perform particle image velocimetry (PIV ) and planar laser induced fluorescence (PLIF) measurements in the model c ombustor chamber. Then we performed simultaneous velocity and scalar field measurements\, characterized the velocity and scalar field measurements\, and examined the possible connections between two fields.\nZoom Meeting CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/95930528324 END:VEVENT BEGIN:VEVENT UID:0-189@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220302T133000 DTEND;TZID=Asia/Jerusalem:20220302T143000 DTSTAMP:20230108T145922Z URL:https://aerospace.technion.ac.il/events/investigation-of-submerged-wat er-breathing-marine-ramjet/ SUMMARY:Investigation of Submerged Water-Breathing Marine Ramjet DESCRIPTION:Lecturer:Nachum-Eliyahu Eisen\n Faculty:Department of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Loc ation:Classroom 165\, ground floor\, Library\, Aerospace Eng & https://tec hnion.zoom.us/j/98452539510\n Zoom: \n Abstract: \n Details: \n The resear ch presents a novel approach for propelling high-speed\, submerged\, marin e vehicles. The operating principle is based on the operation of a ram-roc ket (ducted-rocket) motor (solid or hybrid)\, where water is introduced th rough an inlet due to the vehicle motion\, and mixed with the hot propella nt gases. Theoretical predictions reveal specific impulse increase as high as 70% for non-water-reactive propellants\, and over 100% for water-react ive propellants containing aluminum or magnesium\, relatively to a paralle l non-water-breathing motor. The increase in specific impulse means a subs tantial increase in range and operating time.  Static firing tests of hyb rid motors without and with water addition revealed major increase in thru st and standard specific impulse\, reaching a peak of 485 s due to water a ddition when using polyester fuel containing 30% magnesium (twice the spec ific impulse of a solid rocket). A series of underwater tests of hybrid ra m-rockets in the lab pool at cruise speeds as high as 25 m/s (90 km/h) dem onstrated ignition\, sustained combustion\, and noticeable pressure build- up in the combustion chamber due to incoming water through the nose inlet. Such underwater experiments are unique and had never been published befor e in the open literature.\nThe presentation will include video clips of un derwater operation of a water-breathing ducted-rocket vehicle. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng & https://t echnion.zoom.us/j/98452539510 END:VEVENT BEGIN:VEVENT UID:0-205@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220307T133000 DTEND;TZID=Asia/Jerusalem:20220307T143000 DTSTAMP:20230403T100430Z URL:https://aerospace.technion.ac.il/events/development-and-implementation -of-optimal-strategies-for-constrained-motion-planning/ SUMMARY:Development and Implementation of Optimal Strategies for Constraine d Motion Planning DESCRIPTION:Lecturer:Bhargav Jha\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng & https://technion.zoo m.us/j/98898727601\n Zoom: \n Abstract: \n Details: \n The deployment of a utonomous vehicles in several domains requires efficient planning and trac king of trajectories that can satisfy constraints pertaining to the operat ing environment and the vehicle's kinematics\, while minimizing a suitabl e performance index. Catering to it\, in this talk\, we will discuss optim al planning and tracking of trajectories with the primary focus on applica tions like autonomous delivery systems\, surveillance\, and collision avoi dance.\nWe will begin with the characterization and computation of an exac t time-optimal trajectory between two oriented points via a moving circle for a non-linear Dubins vehicle model. Here\, the moving circle may repres ent a moving obstacle or a neighborhood of interest. The choice of Dubins model is owing to the fact that it is a simple yet sufficiently realistic model to depict a simplified kinematics of fixed-wing unmanned aerial vehi cles\, cars\, and underwater vehicles.\n\nThereafter\, considering the sce narios with multiple vehicles\, we will present a cooperative guidance law for collision avoidance among a heterogeneous team of vehicles in an n-on -n planar engagement scenario. For computational tractability\, in this c ase\, we will discuss the use of a linearized engagement model and minimi zation of team effort of the vehicles as the suitable performance index.\n \nFinally\, for tracking a planned trajectory we will present the applica tion of game-theoretic approaches for precise and robust tracking of aggre ssive trajectories by multirotor platforms. The applicability of this appr oach for Dubins vehicle model will also be demonstrated.\n\nThe talk will also include results from experimental validation of the proposed control methods. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng & https://t echnion.zoom.us/j/98898727601 END:VEVENT BEGIN:VEVENT UID:0-212@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220321T133000 DTEND;TZID=Asia/Jerusalem:20220321T143000 DTSTAMP:20230403T122154Z URL:https://aerospace.technion.ac.il/events/understanding-aerodynamic-prin ciples-toward-air-vehicle-design-and-analysis/ SUMMARY:Understanding Aerodynamic Principles toward Air Vehicle Design and Analysis DESCRIPTION:Lecturer:Dr. Camli Badrya\n Faculty:Institute of Fluid Mechanic s\n Institute:University of Braunschweig\n Location:https://technion.zoom. us/j/94912022701\n Zoom: \n Abstract: \n Details: \n The design and develo pment of high-performance\, efficient\, and sustainable aircraft for a wid e range of applications requires a fundamental understanding of the underl ying aerodynamic principles. For instance\, the aerodynamic phenomena that govern micro air vehicles (MAVs) flight are drastically different from th at of a fixed-wing aircraft flying at transonic speeds. While high fidelit y CFD and experimental methods can help unravel the physics\, for design p urposes\, robust and efficient tools are required. The seminar would focus on the foundational studies we conducted to understand the aerodynamic pr inciples related to two applications operating in different flight regimes and how the knowledge gained is integrated into aircraft design.\n\n\n Large gust encounters for UAM: Wing response to large transverse gusts has become an active area of research\, driven by the demand for both manned and unmanned air vehicles including urban air mobility (UAM) applications. Because of their relatively small size\, these vehicles are more likely t o respond adversely to large gust disturbances during flight. They operate at relatively lower Reynolds numbers where the effects of viscosity could be significant\, and control models and design optimization rely strongly on how accurately the aerodynamic forces during wing–gust interactions can be predicted. The key research questions we are trying to answer are: Can the classical unsteady theory (mainly Kussner-based) capture the wing aero response during larger traverse gust encounters? And how can wing-gus t interaction be modeled efficiently?\n LFC for green aviation: Future e nergy-efficient aircraft require a drastic reduction in drag. The flow on a state-of-the-art commercial airplane wing is turbulent. The laminar flow control (LFC) technique offers large potential for drag reduction. LFC is an active boundary-layer control\, usually by utilizing wall suction to r etain laminar flow and delay transition from laminar-to-turbulent flow. LF C technique can be employed on the lifting and non-lifting surfaces (i.e.\ , wing\, fin\, and fuselage) resulting in reduced skin-friction drag. Our current research focuses on optimizing a wing for LFC application and inve stigating how to integrate the LFC technology into the overall aircraft de sign.\n CATEGORIES:Seminars LOCATION:https://technion.zoom.us/j/94912022701 END:VEVENT BEGIN:VEVENT UID:0-206@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220330T133000 DTEND;TZID=Asia/Jerusalem:20220330T143000 DTSTAMP:20230403T112524Z URL:https://aerospace.technion.ac.il/events/the-role-of-continuous-gust-an d-prescribed-motion-on-blade-aerodynamics-and-broadband-noise/ SUMMARY:The role of continuous gust and prescribed motion on blade aerodyna mics and broadband noise DESCRIPTION:Lecturer:Ilya Lesovoy\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.z oom.us/j/96534148664\n Zoom: \n Abstract: \n Details: \n A wide range of d evices employ airfoils operating at relatively low chord Reynolds numbers and unsteady flow conditions\, such as UAV’s and wind turbines. The proc ess of designing airfoils for those devices relies upon numerical simulati ons using both panel codes (XFOIL) and Navier-Stokes solvers (CFD)\, which predictions are in fair agreement with the experimental data for thin air foils far below aerodynamic stall. Moreover\, those methods lack in predic tion of unsteady flows or pitching movement\, which is regarded as a repre sentative example of an unsteady flow. When an airfoil passes through unst eady flow in pitching motion\, pressure fluctuations are generated on its surface in a way that is not fully verified. To widen the knowledge on aer odynamic characteristics on airfoil in pitching motion and unsteady flow\, NACA 0018 airfoil was manufactured and tested in closed loop wind tunnel. A novel rig design allowed a harmonical pitching motion\, while passive g rids generate turbulent flow inside the wind tunnel. A dense chordwise dis tribution of pressure taps allowed time-resolved surface pressure measurem ents that are used to experimentally investigate aerodynamic forces and ch aracteristics of the separation of the flow over the airfoil in comparison to static conditions. The experimental setup allows a variation of mean p itching angles and amplitudes\, Reynolds numbers and turbulence intensitie s. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/96534148664 END:VEVENT BEGIN:VEVENT UID:0-213@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220425T133000 DTEND;TZID=Asia/Jerusalem:20220425T143000 DTSTAMP:20230403T122301Z URL:https://aerospace.technion.ac.il/events/wing-dynamic-shape-sensing-fro m-fiber-optic-strain-data-using-the-kalman-state-estimator/ SUMMARY:Wing Dynamic Shape-Sensing From Fiber-Optic Strain Data Using the K alman State Estimator DESCRIPTION:Lecturer:Tsoof Joels\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zo om.us/j/92528464038\n Zoom: \n Abstract: \n Details: \n New aircraft desig ns are more flexible than ever before\, making them susceptible to adverse aeroelastic phenomena such as a large dynamic response to atmospheric tur bulence and even flutter. On the other hand\, some studies suggest that wi ng flexibility can be leveraged to achieve optimal performance. This motiv ated the aeroelastic community to develop methods for sensing the deformed shape of flexible wings in-flight. The current research study proposes a novel method for shape sensing that is based on strain data\, an aeroelast ic model\, and the use of the Kalman state estimator.\nSeveral recent stud ies proposed different methods in which strain data\, measured in optical fibers\, can be used to estimate the deformed shape of a flexible wing. Fi ber optic sensors typically provide accurate\, high-resolution strain data \, yielding accurate estimates of a wing's deformed shape. However\, the s train data could be imperfect (for example\, due to saturation or temperat ure effects)\, corrupted\, or missing. The current study proposes to use a Kalman state estimator that weighs strain data and simulation output of a n aeroelastic model to estimate wing deformations. The method is demonstra ted in a wind-tunnel test of a flexible wing model excited by prescribed c ontrol surface deflections. Fiber Bragg Grating sensors embedded in two op tical fibers over the wing's span measure strains\, which are used to esti mate the wing deformations. The latter are compared to wing deformations m easured by a motion recovery camera system. Results show the advantages of the proposed method when the strain data or the aeroelastic model are imp erfect. Additionally\, the method provides  smooth estimates of the modal velocities readily available for use by the vehicle's control system. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/92528464038 END:VEVENT BEGIN:VEVENT UID:0-208@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220523T133000 DTEND;TZID=Asia/Jerusalem:20220523T143000 DTSTAMP:20230403T121735Z URL:https://aerospace.technion.ac.il/events/performance-and-control-of-mul tirotors-formation-with-slung-load-in-an-urban-environment/ SUMMARY:Performance and Control of Multirotors Formation with Slung Load in an Urban Environment DESCRIPTION:Lecturer:Amit Weinreb\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.z oom.us/j/91293264013\n Zoom: \n Abstract: \n Details: \n The use of small unmanned aerial vehicles (UAV) has extensively increased during the last d ecade. Their most common applications are in sport events’ photography\, search-and-rescue missions and military reconnaissance. Additional area w ith potentially rapid growth is the autonomous deliveries. Using small mul ti-rotor drones to deliver door-to-door has many benefits\, ranging from r educing shipping time and costs to high reliability and convenience. The d rawback is a relatively small lifting capacity of currently operational mu lti-rotor UAVs. It can be mitigated\, to some extent\, by employing a form ation of UAVs to the same task.\nDesigning a control algorithm for a forma tion of multi-rotor-UAVs carrying a sling load is a challenging task\, not only because of the complexity of the formation’s dynamics\, but also b ecause of the complexity of the rotors’ aerodynamics. Normally\, a simpl ified aerodynamic model is adopted\, in which the forces and moments gener ated by a rotor are determined solely by its rotational speed. In this stu dy the simplified aerodynamic model is replaced by a realistic one.  It i s demonstrated that the commonly used model is inadequate in windy environ ment\, especially in urban areas where wind gradients are large. By exposi ng a formation of four quad-rotor UAV’s carrying a sling load to turbule nt winds\, it is shown that a ‘standard’ trajectory tracking guidance with force controller\, designed using the simplified model\, can crash. A n update to the original controller scheme is suggested\, to improve the s ystem performance. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/91293264013 END:VEVENT BEGIN:VEVENT UID:0-207@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220525T133000 DTEND;TZID=Asia/Jerusalem:20220525T143000 DTSTAMP:20230403T121602Z URL:https://aerospace.technion.ac.il/events/modal-rotations-a-modal-based- method-for-large-structural-deformations/ SUMMARY:Modal Rotations: A Modal-based Method for Large Structural Deforma tions DESCRIPTION:Lecturer:Ariel Drachinsky\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https://techni on.zoom.us/j/92330966203\n Zoom: \n Abstract: \n Details: \n Modern flight configurations are trending towards slender wings of larger wingspans and lower structural weight. New designs are driven by performance requiremen ts (reduction of fuel consumption\, or flight at the boundary of the atmos phere\, for example) as well as by innovations in softer materials (such a s polymers used in rapid prototyping). These result in configurations that are lighter but more flexible than before. For very flexible configuratio ns\, the industry-standard computational formulations based on linear stru ctural models are no longer adequate. Consequently\, novel\, nonlinear str uctural models are being developed for the aeroelastic analysis of structu res that experience large deformations. Due to their complexity\, nonlinea r structural models tend to be either limited to simple geometries (beams\ , for example) or highly detailed and computationally expensive (nonlinear finite-element models). The study presents the derivation and applicatio n of the Modal Rotation Method (MRM)\, a nonlinear framework for the static and flutter analysis of highly flexible\, slender wing-like stric tures accounting for large deformations. It uses a linear modal database  which makes it easy to use\, and computationally efficient. The framewo rk is used both for the analysis of slender structures under prescribed fl ight conditions and as a part of a nonlinear strain-based shape sensing al gorithm. The talk will focus on the MRM formulation and its validation\, b oth numerically and experimentally\, with several test cases including th e Pazy wing aeroelastic benchmark for large deformations\, and will then b riefly present the MRM strain-based a shape sensing application. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https:// technion.zoom.us/j/92330966203 END:VEVENT BEGIN:VEVENT UID:0-209@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220530T133000 DTEND;TZID=Asia/Jerusalem:20220530T143000 DTSTAMP:20230403T121921Z URL:https://aerospace.technion.ac.il/events/space-programs-why-and-how/ SUMMARY:Space Programs: Why and How DESCRIPTION:Lecturer:Dmitry Payson\n Faculty:\n Institute:\n Location:Class room 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zo om.us/j/93657669627\n Zoom: \n Abstract: \n Details: \n The presentation p rovides an overview of the space program and industry system research and education efforts performed in recent years. It is concentrated at Why's a nd How's of the national space program and industry restructuring efforts and corresponded institutional design exercises. Basically\, this lecture summarizes the efforts of building ‘the space program with the human fac e’. The key topics include (1) A practical example of the national space industry restructuring effort in 2010-2015\; (2) Actual issues of the spa ce markets’ modelling\; (3) An overview of the public goods concept appl ication to the space economics\; (4) Skolkovo\, a brave endeavor for the p rivate space greenfield. In additional\, the vision of the actual economic research topics will be provided addressing the current international spa ce market and industry development\, like New Space\, space resources comm ercialization et al. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https: //technion.zoom.us/j/93657669627 END:VEVENT BEGIN:VEVENT UID:0-10@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220720T170000 DTEND;TZID=Asia/Jerusalem:20220720T190000 DTSTAMP:20221030T083450Z URL:https://aerospace.technion.ac.il/events/519/ SUMMARY:Aerospace Department Excellent Students' Ceremony DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Auditorium (ro om no. 235)\n Zoom: \n Abstract: \n Details: \n Fellowships\, awards and e xcellence certificates for the 2012-2013 academic year achievements. CATEGORIES:Events LOCATION:Auditorium (room no. 235) END:VEVENT BEGIN:VEVENT UID:0-8@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20220720T180000 DTEND;TZID=Asia/Jerusalem:20220720T190000 DTSTAMP:20221030T083451Z URL:https://aerospace.technion.ac.il/events/auvsi-project-conclusion-and-p resentation-evening-2015/ SUMMARY:AUVSI Project Conclusion and Presentation Evening 2015 DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Aerospace Facu lty Auditorium\, room no. 235\n Zoom: \n Abstract: \n Details: \n The auto nomous airborne system\, designed\, built and flown by a joint team of stu dents from the faculties of Aerospace Engineering and Electrical Engineeri ng\, will be presented at the event. CATEGORIES:Events LOCATION:Aerospace Faculty Auditorium\, room no. 235 END:VEVENT BEGIN:VEVENT UID:0-55@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221024T090000 DTEND;TZID=Asia/Jerusalem:20221024T180000 DTSTAMP:20221030T083453Z URL:https://aerospace.technion.ac.il/events/winter-semester-2022-23-openin g/ SUMMARY:Winter Semester 2022/23 Opening DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:\n Location:\n Zoom: \n Abstract: Winter Semester 2022-2023 Opening.\ n\nIntroductory day to new Aerospace Engineering students\n\n \;\n Det ails: \n CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-11@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221024T133000 DTEND;TZID=Asia/Jerusalem:20221024T143000 DTSTAMP:20221030T083453Z URL:https://aerospace.technion.ac.il/events/new-seminar/ SUMMARY:Investigation of the effect of water-in-fuel emulsion spray on an e dge flame DESCRIPTION:Lecturer:Ohad Shalev-Eggert\n Faculty:Department of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:\n Zoom: https://technion.zoom.us/j/98800929742\n Abstract: Water-in-f uel emulsion droplets are comprised of an inner water droplet immiscible w ith\, and surrounded by\, an outer liquid fuel layer. As part of the world wide effort to reduce pollution emissions from combustion processes\, the use of such liquid droplets is considered as a means to increase combustio n efficiency and reduce pollutants emissions from existing power systems. This is achieved mainly due to a reduction in the burned gas temperature i nduced by the water content and to secondary droplet atomization\, as pare nt droplets micro-explode producing faster-evaporating smaller offspring d roplets\, leading to better mixing.\n\nIn the current work\, a new two-dim ensional thermal-diffusional model is formulated to describe the edge flam e formed by two laminar co-flowing streams\, one of an oxidant and the oth er of fuel vapor and water-in-fuel emulsion droplets\, separated initially by a splitter plate. A numerical investigation was performed of how the i nitial presence of the water-in-fuel droplets and their micro-explosions e ffect the thermal structure of the compound flame in the mixing layer down stream of the splitter plate. Trends were identified that\, among others\, relate the temperature of different flame zones\, flame location and stab ility\, to the percentage and properties of the water in the emulsion drop lets. These findings contribute to understanding the potential working con ditions\, pros and cons of water-in-fuel emulsions.\n\n \;\n\nMon\, 24 -10-2022\, 13:30-14:30 (Gathering at 13:30)\nClassroom 165\, ground floor\ , Library\, Aerospace Eng.\nZOOM: https://technion.zoom.us/j/98800929742\n Light refreshments will be served before the lecture\n Details: Mon\, 24-1 0-2022\, 13:30-14:30 (Gathering at 13:30)\nClassroom 165\, ground floor\, Library\, Aerospace Eng.\nZOOM: https://technion.zoom.us/j/98800929742\nLi ght refreshments will be served before the lecture\n Ohad Shalev-Eggert\nW ork towards MSc degree under the supervision of Prof. Emeritus J. Barry Gr eenberg (Technion)\nDepartment of Aerospace Engineering\nTechnion – Isra el Institute of Technology ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2022/08/003.jpg CATEGORIES:Seminars END:VEVENT BEGIN:VEVENT UID:0-5@aerospace.technion.ac.il DTSTART:20221026T133000Z DTEND:20221026T143000Z DTSTAMP:20221030T083455Z URL:https://aerospace.technion.ac.il/events/sample-event/ SUMMARY:Numerical Investigation on a Cavity-Based Scramjet Model: Lessons L earnt and Challenges DESCRIPTION:Lecturer:Dr. Donggang Cao\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https:// technion.zoom.us/j/99650193751?pwd=WGxTUFNvMzVLeEpCRmd6eWtDSUdHdz09\n Abst ract: The scramjet engine has been identified as one of the most promising propulsion systems for hypersonic vehicles. The flow in the scramjet rema ins supersonic with a typical residence time of 1 millisecond. Short time scales and the coupling of multiple physics yield a complex flow field in which the flame kernels morph into a reacting vortex ring upon interaction with the supersonic flow\, making mixing enhancement\, ignition\, and fla me stabilization major challenges in the development of scramjet engines.\ n\nA cavity-based scramjet model was designed and a test facility was buil t accordingly at Technion-Israel Institute of Technology. Meanwhile\, the simulation strategy of the scramjet model was set up using a hybrid RANS/L ES method based OpenFOAM\, which is an open source CFD toolbox. Both exper imental and numerical efforts have been made to investigate the combustion characteristics in the scramjet. In this talk\, the complementary results of both approaches will be presented to explore the rich physics in the f low field of the scramjet. We propose a new method to divide the flow fiel d into different regions and decompose the combustion into different modes by using filter functions. The focus is placed on the links among the fue l injection schemes\, flame stabilization locations\, combustion modes\, a nd vorticity transport behaviors in the scramjet. The lessons we’ve lear nt and challenges we’re facing will be summarized\n Details: \n Dr. Dong gang Cao\nPost Doc under the supervision of Asst. Prof. Dan Michaels\nDepa rtment of Aerospace Engineering\nTechnion – Israel Institute of Technolo gy CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-6@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221102T133000 DTEND;TZID=Asia/Jerusalem:20221102T143000 DTSTAMP:20221030T083456Z URL:https://aerospace.technion.ac.il/events/analytical-modeling-of-the-sol ar-radiation-pressure-by-canonical-methods/ SUMMARY:Physics-constrained machine learning in unpredictable fluids DESCRIPTION:Lecturer:Dr. Luca Magri\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: \n Zoom: https://technion.zoom.us/j/95437411538\n Abstract: The ability of fluid mechanics modelling to predict the evolution of a flow is enabled b y physical principles and empirical approaches. Physical principles\, for example conservation laws\, are extrapolative (until the assumptions upon which they hinge break down): they provide predictions on phenomena that have not been observed. Human beings are excellent at extrapolating knowle dge because we are excellent at finding physical principles. Empirical mod elling provides correlation functions within data. Artificial intelligence and machine learning are excellent at empirical modelling. In this talk\,  the complementary capabilities of both approaches will be exploited to achieve adaptive modelling and optimization of nonlinear\, unsteady and un certain flows. The focus of the talk is on computational methodologies for modelling and optimization of increasingly complex flows: (i) data assimi lation with a Bayesian approach for controlling thermoacoustic oscillation s in rockets/gas turbines\, (ii) auto-encoders for reduced-order modelling of turbulent flows\, which generalise POD/DMD methods to nonlinear dynami cs\; and (iii) modelling of multi-phase flows (time permitting). The flows under investigation are relevant to aerospace propulsion\, with a focus o n thermoacoustics\, and turbulence.\n Details: \n Dr. Luca Magri - Guest l ecture - Imperial College London\; The Alan Turing Institute\; University of Cambridge\; Technion (visiting) CATEGORIES:Seminars END:VEVENT BEGIN:VEVENT UID:0-68@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221116T133000 DTEND;TZID=Asia/Jerusalem:20221116T143000 DTSTAMP:20221116T081119Z URL:https://aerospace.technion.ac.il/events/terrain-aided-recovery-of-a-mu ltirotor-using-laser-range-finders-in-a-satellite-navigation-deprived-envi ronment/ SUMMARY:Terrain Aided Recovery of a Multirotor Using Laser Range-Finders in a Satellite-Navigation Deprived Environment DESCRIPTION:Lecturer:Stanislav Shougaev\n Faculty:Department of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Engineering\n Zoom: https://technion.zoom.us/j/6508255931\n Abstract: Unmanned aerial vehicle s rely predominantly on external signal reception for navigation. This inc ludes both satellite navigation (GNSS) and guidance through remote control channels. In case of a signal loss\, a recovery logic is needed to naviga te the vehicle back to its base until normal operation is regained. Such s ystems commonly require pre-installed local maps of the flight area or ric h-information sensors like LIDARs and cameras. \n\nOur work examines a rec overy logic for a multirotor based on several Body-Fixed Laser Range-Finde rs (BF-LRFs) and an inertial measurement unit (INS) without a pre-installe d map\, hence providing a simple\, low-cost recovery solution. BF-LRFs wer e shown to perform well for Terrain Following for single UAVs and multirot or slung load applications. To facilitate the recovery\, a terrain map alo ng the flight trajectory can be constructed during the normal GNSS operati on when an accurate navigation solution is available using the BF-LRFs as terrain sampling sensors. In case of GNSS signal loss\, the accumulated ma p\, together with an INS and the BF-LRFs measurements\, are used for a ter rain-aided navigation type solution to navigate the vehicle back to its ba se. Along with the recovery system\, a BF-LRF based obstacle avoidance sol ution is examined both separately from the recovery system and combined. T he recovery logic was tested in a realistic six-degrees-of-freedom simulat ion using a real terrain map. The simulations evaluated the recovery and t he obstacle avoidance systems in several different LRF configurations and flight paths\, showing promising results.\n\n \;\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Engineering END:VEVENT BEGIN:VEVENT UID:0-1198@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221205T013000 DTEND;TZID=Asia/Jerusalem:20221205T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2022-12-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1199@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221207T013000 DTEND;TZID=Asia/Jerusalem:20221207T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2022-12-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1200@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221212T013000 DTEND;TZID=Asia/Jerusalem:20221212T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2022-12-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1201@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221214T013000 DTEND;TZID=Asia/Jerusalem:20221214T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2022-12-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1202@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221219T013000 DTEND;TZID=Asia/Jerusalem:20221219T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2022-12-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-181@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221219T133000 DTEND;TZID=Asia/Jerusalem:20221219T143000 DTSTAMP:20221208T143421Z URL:https://aerospace.technion.ac.il/events/science-and-engineering-of-ele ctric-propulsion/ SUMMARY:Science and Engineering of Electric Propulsion DESCRIPTION:Lecturer:Michael Keidar\, A. James Clark Professor of Engineeri ng\n Faculty:Department of Mechanical and Aerospace Engineering Department of Biomedical Engineering (secondary appointment)\n Institute:School of E ngineering and Applied Science The George Washington University\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://t echnion.zoom.us/j/98367931661\n Abstract: Electric propulsion has become p opular nowadays owing to the trend of miniaturizing the size and mass of s atellites. In this talk we will discuss some recent trend\, advances and p erspectives of electric propulsion in both low-power and high-power limits .\nOne of main drawback of the most popular approach\, Hall thrusters\, is that their efficiency and thrust-to-power ratio significantly deteriorate when its size and power level are reduced. We will discuss some alternati ve approach—a low-power (<\;50 W)\, lightweight (~100 g)\, two-stage p ropulsion system. The system is based on a micro-cathode arc thruster with magnetoplasmadynamic second stage (mCAT-MPD)\, which achieves the followi ng parameters: a thrust of up to 1.7 mN at a TPR of 37 mN/W and an efficie ncy of about 50%. This thruster\, in addition to “traditional” inverse \, displays the anomalous direct (growing) “TPR versus specific impulse Isp” trend at high Isp values and allows multimodality at high efficienc y.\nIn the high-power limit\, multiple configurations of air-breathing thr usters are currently considered. This talk will outline state of the art a nd will present some new development such as scramjet configuration that c an significantly reduce the drag by avoiding compression. In addition\, co ncept of air—breathing plasma thruster without neutralizer will be discu ssed.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1203@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221221T013000 DTEND;TZID=Asia/Jerusalem:20221221T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2022-12-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-74@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221221T133000 DTEND;TZID=Asia/Jerusalem:20221221T143000 DTSTAMP:20221214T080124Z URL:https://aerospace.technion.ac.il/events/autonomous-scalable-and-robust -fusion-for-collaborative-robotic-bayesian-inference/ SUMMARY:Autonomous\, Scalable and Robust Fusion for Collaborative Robotic B ayesian Inference DESCRIPTION:Lecturer:Ofer Dagan\n Faculty:Aerospace Engineering Sciences De partment \n Institute:University of Colorado Boulder\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://cuboulder.zo om.us/j/93825793193\n Abstract: The idea of a robotic team cooperating on a joint task can be allegorized to a group of people working together. Oft en people have different capabilities\, different knowledge\, and differen t worldviews. However\, when collaborating\, people naturally know how to summarize only the relevant information to achieve a joint goal. For a tea m of robots that needs to work together\, this human capability is not tri vial. The robot's ability to make sense and act in a constantly changing e nvironment is much less effective than what the human brain does.\nMy goal is to enable teams of robots to collaborate in a robust\, autonomous\, an d scalable manner on a variety of complementary tasks. Toward this goal I take a probabilistic approach to robotics\, where a robot models the uncer tainty in how it perceives the world using a probability distribution (pdf ). In Bayesian decentralized data fusion (DDF) this approach is leveraged to allow any two robots in a network to gain new data by sharing their pos terior pdfs\, representing their estimate. However\, DDF methods do not sc ale well as the number of robots in the network increase\, since they freq uently require all robots to process and communicate the full global pdf. In this talk I will show how the global problem can be “broken” into s maller locally relevant problems\, thus significantly improves communicati on and computation requirements for each robot. I will present new scalabl e algorithms and demonstrate their applicability to collaborative inferenc e problems with simulations and hardware experiments on robotic platforms. \n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1204@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221226T013000 DTEND;TZID=Asia/Jerusalem:20221226T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2022-12-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-182@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221226T133000 DTEND;TZID=Asia/Jerusalem:20221226T143000 DTSTAMP:20221214T073829Z URL:https://aerospace.technion.ac.il/events/long-term-bounded-satellite-fo rmation-flying-around-mars-and-the-martian-moons/ SUMMARY:Long-term Bounded Satellite Formation Flying around Mars and the Ma rtian Moons DESCRIPTION:Lecturer:Guy Marcus \n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://techn ion.zoom.us/j/98367931661\n Abstract: The interest in the Martian system h as increased over the past decades\, as more studies indicate that Mars wa s once habitable and may preserve subsurface lakes. Establishing long-term bounded satellite formation flying about Mars is an important effort in t he exploration of the Martian system. In this research\, we focused on the dynamics around Mars and the Martian Moons\, as a part of that effort. In this talk\, we will discuss three endeavours taken for modelling and anal ysing different regions in the Martian system. One region is beyond the ra dii of the Martian moons. This is the first study to model the long-term d ynamics in such an environment. The second region is low Mars orbits. In t his region\, we focused on establishing long-term bounded satellite format ion flying around Mars. The third region is the vicinity of the Martian mo ons\, Phobos and Deimos. Studying the dynamics nearby the Martian moons ca n provide important information on the evolution of science orbits for Mar tian moon exploration. In that context\, we focused on finding the exact l ocation of the libration points adjacent to the moons - where potential ex ploration spacecraft can reside in a stable position or a periodic orbit.\ n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1205@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20221228T013000 DTEND;TZID=Asia/Jerusalem:20221228T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2022-12-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1206@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230102T013000 DTEND;TZID=Asia/Jerusalem:20230102T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1207@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230104T013000 DTEND;TZID=Asia/Jerusalem:20230104T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-72@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230105T090000 DTEND;TZID=Asia/Jerusalem:20230105T170000 DTSTAMP:20221201T201514Z URL:https://aerospace.technion.ac.il/events/technoin-open-day/ SUMMARY:Technoin Open Day DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:\n Zoom: \n Ab stract: \n Details: \n Do you think about studying at the Technion? The op en day for candidates is your opportunity to get to know the different opt ions and routes up close.\n\nOn this day\, those interested in studying fo r a bachelor's degree in Aerospace Engineering will have the opportunity t o enjoy a glimpse into the faculty\, its research and study topics\, cours es\, excellence programs\, and more. Registration for the Technion for the year 2023 (October 2023) is open\, and you deserve to receive all the det ails that will help you choose the #highest_studies_there_is.\n\n CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-73@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230105T093000 DTEND;TZID=Asia/Jerusalem:20230105T160000 DTSTAMP:20221201T202235Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%a4%d 7%aa%d7%95%d7%97-%d7%9c%d7%9e%d7%aa%d7%a2%d7%a0%d7%99%d7%99%d7%a0%d7%99%d7 %9d/ SUMMARY:יום פתוח למתעניינים DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n חושבים על לימודים בטכניון? יום המתעניינים הוא ההזדמנות שלכם להכיר את מ קרוב את האפשרויות והמסלולים השונים.\n\nלמ תעניינים בלימודי תואר ראשון בהנדסת אווי רונאוטיקה וחלל ניתן ביום זה הצצה אל תוך ה פקולטה\, נושאי המחקר והלימודים בה\, מבנה ב לימודים\, תכניות המצוינות\, המסלול המשותף אווירו-פיזיקה ועוד. ההרשמה לטכניון לשנה ”ל תשפ”ג (אוקטובר 2023) פתוחה ולכם מגיע לק בל את כל הפרטים שיעזרו לכם לבחור את #הלימ ודים_הכי_גבוהים_שיש.\n\n \;\n\n CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-1208@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230109T013000 DTEND;TZID=Asia/Jerusalem:20230109T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1209@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230111T013000 DTEND;TZID=Asia/Jerusalem:20230111T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1210@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230116T013000 DTEND;TZID=Asia/Jerusalem:20230116T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-185@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230116T133000 DTEND;TZID=Asia/Jerusalem:20230116T143000 DTSTAMP:20230103T081414Z URL:https://aerospace.technion.ac.il/events/two-dimensional-and-three-dime nsional-buffet-flows-characterization-and-their-role-in-aeroelastic-instab ilities/ SUMMARY:Two-Dimensional and Three-Dimensional Buffet Flows Characterization and Their Role in Aeroelastic Instabilities DESCRIPTION:Lecturer:Lior Poplingher\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://t echnion.zoom.us/j/98367931661\n Abstract: Shock buffet is an aerodynamic i nstability characterized by self-sustained shock oscillations\, which occu rs at transonic Mach numbers and moderate angles-of-attack on both airfoil (two-dimensional\, 2D) and wing (three-dimensional\, 3D) configurations. The variation of the aerodynamic coefficients degrades handling qualities and aerodynamic performance\, eventually limiting flight envelopes. Furthe rmore\, the shock oscillations occur at frequencies close to the natural m odes of wings\, thus\, might lead to unstable structural interactions.\nAl though many studies were performed on 2D configurations\, the understandin g of the fundamental mechanism of the rigid 3D shock buffet and its intera ction with elastic wing structures is still limited.  A better understand ing of these two issues is essential for structural design of transonic ai rcraft and can support the development of control strategies for buffet su ppression in realistic flight configurations.\nThe current study presents a computational investigation using Unsteady Reynolds-Averaged Navier-Stok es simulations and modal analysis of the shock buffet on 3D configurations \, its distinction from 2D shock buffet\, and the fluid-structure interact ion between the 3D shock buffet flow and wing elasticity in finite wings.\ n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1211@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230118T013000 DTEND;TZID=Asia/Jerusalem:20230118T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1212@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230123T013000 DTEND;TZID=Asia/Jerusalem:20230123T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1213@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230125T013000 DTEND;TZID=Asia/Jerusalem:20230125T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-190@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230125T173000 DTEND;TZID=Asia/Jerusalem:20230125T190000 DTSTAMP:20230123T164757Z URL:https://aerospace.technion.ac.il/he/events/%d7%98%d7%a7%d7%a1-%d7%94%d 7%a2%d7%a0%d7%a7%d7%aa-%d7%aa%d7%a2%d7%95%d7%93%d7%95%d7%aa-%d7%94%d7%a6%d 7%98%d7%99%d7%99%d7%a0%d7%95%d7%aa/ SUMMARY:טקס הענקת תעודות הצטיינות DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n טקס הענקת תעודות הצטיינות לסט ודנטים בגין הישגיהם בסמסטר חורף ו/או אבי ב תשפ"ב:\n• מצטייני דיקן\n• מצטייני נשיא\n\ nבמסגרת הטקס יוענקו גם מספר פרסים לסטודנ טים בלימודי הסמכה ובלימודי מוסמכים:\n• פ רס סגינר למצוינות ראויה במחקר\n• פרס רוב ין לעבודה מצטיינת\n• פרס שטרנברג להמצאה חדשנית בתחום האווירונאוטיקה\n• פרס בעיל ום שם למצוינות במחקר CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-191@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230125T173000 DTEND;TZID=Asia/Jerusalem:20230125T190000 DTSTAMP:20230124T061519Z URL:https://aerospace.technion.ac.il/events/certificates-of-excellence-awa rding-ceremony/ SUMMARY:Certificates of excellence awarding ceremony DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n The ceremony of awarding certificates of excellence to students for their achievements in the winter and/or spring semesters of 2 022\n\n Dean's excellence certificates\n President’s excellence certif icates\n\n \;\n\nAs part of the ceremony\, four awards for outstanding achievements will also be given to undergraduate and graduate students. CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-1214@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230130T013000 DTEND;TZID=Asia/Jerusalem:20230130T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-01-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-187@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230130T133000 DTEND;TZID=Asia/Jerusalem:20230130T143000 DTSTAMP:20230103T081518Z URL:https://aerospace.technion.ac.il/events/resilient-navigation-augmentin g-inertial-navigation-systems-with-satellite-signals-of-opportunity/ SUMMARY:Resilient Navigation: Augmenting Inertial Navigation Systems with S atellite Signals of Opportunity DESCRIPTION:Lecturer:Ariel Baron \n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://tech nion.zoom.us/j/98367931661\n Abstract: In a GNSS-denied environment\, it i s important to have alternative navigation systems that can provide accura te and reliable positioning\, navigation\, and timing (PNT) information. T his is particularly critical in scenarios where PNT is essential for safet y or mission-critical applications\, such as in aviation\, maritime naviga tion\, and military operations.\nThis research aims to develop a 4D (posit ion/navigation/time) system by passively receiving downlink signals from l arge constellations of low Earth orbit satellites\, such as OneWeb\, Starl ink\, and GlobalStar. These constellations will not support pseudorange-ba sed navigation because they will not carry atomic clocks and will not broa dcast downlink signals that support pseudorange measurements. Instead\, th e system will use carrier Doppler shift as the only navigation observable\ , using eight or more measurements to determine 3D position\, receiver clo ck offset\, velocity\, and receiver clock offset rate.\nThe research focus ed on a Doppler shift measurement model. Convergence techniques for non-li near optimization were explored and the expected accuracy was evaluated th rough the development of Geometric Dilution of Precision (GDOP) formulatio ns. A simulator was developed to assess navigation performance in static e nvironments and predict GDOP at any given time and receiver location. Addi tionally\, the research included a hardware implementation on a smartphone device as well as investigation into the effect of atmospheric and orbita l errors on the navigation system.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1215@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230201T013000 DTEND;TZID=Asia/Jerusalem:20230201T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-02-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1216@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230206T013000 DTEND;TZID=Asia/Jerusalem:20230206T023000 DTSTAMP:20251118T063934Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-02-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1217@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230208T013000 DTEND;TZID=Asia/Jerusalem:20230208T023000 DTSTAMP:20251118T063933Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-02-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1218@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230213T013000 DTEND;TZID=Asia/Jerusalem:20230213T023000 DTSTAMP:20251118T063933Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-02-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1219@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230215T013000 DTEND;TZID=Asia/Jerusalem:20230215T023000 DTSTAMP:20251118T063933Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-02-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1220@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230220T013000 DTEND;TZID=Asia/Jerusalem:20230220T023000 DTSTAMP:20251118T063933Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-02-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1221@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230222T013000 DTEND;TZID=Asia/Jerusalem:20230222T023000 DTSTAMP:20251118T063933Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-02-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1222@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230227T013000 DTEND;TZID=Asia/Jerusalem:20230227T023000 DTSTAMP:20251118T063933Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-02-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1223@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230301T013000 DTEND;TZID=Asia/Jerusalem:20230301T023000 DTSTAMP:20251118T063933Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1224@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230306T013000 DTEND;TZID=Asia/Jerusalem:20230306T023000 DTSTAMP:20251118T063933Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1225@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230308T013000 DTEND;TZID=Asia/Jerusalem:20230308T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-193@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230308T133000 DTEND;TZID=Asia/Jerusalem:20230308T143000 DTSTAMP:20230308T113823Z URL:https://aerospace.technion.ac.il/events/development-of-an-additive-man ufactured-micro-gas-turbine/ SUMMARY:Development of an Additive Manufactured Micro Gas Turbine DESCRIPTION:Lecturer:Lukas Badum\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://techn ion.zoom.us/j/98367931661\n Abstract: \n Details: \n Ultra micro gas turbi nes for electric power generation below 1 kW are a viable replacement tech nology for lithium batteries in drones due to their high energy density. T o achieve high aerodynamic efficiency\, turbomachinery at centimeter scale and speeds up to 500\,000 rpm are required. Previous research showed that small-scale effects disqualify design practices applied to larger gas tur bines where subcomponents can be optimized isolated from system design. To appropriately capture component interdependencies of ultra micro gas turb ines\, an integrated design approach based on reduced order models is expe dient. Therefore\, a comprehensive engine design model including thermodyn amic cycle analysis\, compressor and turbine aerodynamic design\, combusto r design and high-speed generator design is presented. The design system i s adapted to capture additive manufacturing constraints of small-scale com ponents. In addition\, reduced order models for rotordynamics\, stress ana lysis and heat transfer are used to define the permissible design space.\n To validate the established set of reduced order models\, extensive experi mental investigations have been performed. The applicability of additive m anufacturing to micro gas turbines was investigated by performance compari son of two rotors manufactured with lithographic ceramic manufacturing (LC M) and selective laser sintering (SLS). To this end\, compressor performan ce maps were recorded at speeds up to 450\,000 rpm\, showing significant p erformance benefit for the LCM processed rotor and good agreement with the reduced order model. Additionally\, porous media combustion performance w as measured\, showing low achievable equivalence ratios but considerable r adiation heat losses. Furthermore\, a high-speed generator was developed a nd tested validating the reduced order modelling approach. Finally\, syste m performance testing is currently on-going on a preliminary micro turbine prototype integrating generator\, turbomachinery and combustor. CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1226@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230313T013000 DTEND;TZID=Asia/Jerusalem:20230313T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-192@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230313T133000 DTEND;TZID=Asia/Jerusalem:20230313T143000 DTSTAMP:20230228T084626Z URL:https://aerospace.technion.ac.il/events/hypergolic-ignition-of-kerosen e-based-gel-fuel-with-hydrogen-peroxide-in-rocket-motors/ SUMMARY:Hypergolic Ignition of Kerosene-Based Gel Fuel with Hydrogen Peroxi de in Rocket Motors DESCRIPTION:Lecturer:Roni Goldin\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://techn ion.zoom.us/j/97346140543\n Abstract: The present work seeks to characteri ze the hypergolic ignition of a proprietary propellant. It consists of hyd rogen peroxide as oxidizer\, a kerosene-based gel fuel and a certain amoun t of sodium borohydride as an energetic additive.\n An experimental parame trical investigation was conducted in order to correlate between different physical and chemical parameters that affect ignition delay times. The af orementioned parameters are Weber and Reynolds numbers\, momentum\, kineti c energy and hydrogen peroxide concentration. The videos of the conducted drop-on-drop test were analyzed using digital image processing. The phenom enon of ignition and combustion of the gelled fuel was divided into two ma in events: the "Primary Ignition" and the "Fuel Ignition". These delay tim es were calculated and plotted versus all different parameters and analyze d.\nIncrease in momentum and kinetic energy led to about 40% reduction in both primary and fuel ignition delay times. Usage of 90% hydrogen peroxide led to decrease of more than 20 ms compared to 70% hydrogen peroxide. Min imal ignition delay times of 4-5 ms were observed.\n\n Details: \n LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-194@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230313T133000 DTEND;TZID=Asia/Jerusalem:20230313T143000 DTSTAMP:20230504T121802Z URL:https://aerospace.technion.ac.il/events/hypergolic-ignition/ SUMMARY:Hypergolic Ignition of Kerosene-Based Gel Fuel with Hydrogen Peroxi de in Rocket Motors DESCRIPTION:Lecturer:Roni Goldin\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng\n Zoom: https://techni on.zoom.us/j/97346140543\n Abstract: The present work seeks to characteriz e the hypergolic ignition of a proprietary propellant. It consists of hydr ogen peroxide as oxidizer\, a kerosene-based gel fuel and a certain amount of sodium borohydride as an energetic additive.\nAn experimental parametr ical investigation was conducted in order to correlate between different p hysical and chemical parameters that affect ignition delay times. The afor ementioned parameters are Weber and Reynolds numbers\, momentum\, kinetic energy and hydrogen peroxide concentration. The videos of the conducted dr op-on-drop test were analyzed using digital image processing. The phenomen on of ignition and combustion of the gelled fuel was divided into two main events: the "Primary Ignition" and the "Fuel Ignition". These delay times were calculated and plotted versus all different parameters and analyzed. \nIncrease in momentum and kinetic energy led to about 40% reduction in bo th primary and fuel ignition delay times. Usage of 90% hydrogen peroxide l ed to decrease of more than 20 ms compared to 70% hydrogen peroxide. Minim al ignition delay times of 4-5 ms were observed.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-69@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem;VALUE=DATE:20230315 DTEND;TZID=Asia/Jerusalem;VALUE=DATE:20230317 DTSTAMP:20221111T203929Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%9b%d7%a0%d7%a1-%d 7%94%d7%99%d7%a9%d7%a8%d7%90%d7%9c%d7%99-%d7%94%d7%a9%d7%a0%d7%aa%d7%99-%d 7%94-62-%d7%9c%d7%9e%d7%93%d7%a2%d7%99-%d7%94%d7%aa%d7%a2%d7%95%d7%a4%d7%9 4-%d7%95%d7%94%d7%97/ SUMMARY:הכנס הישראלי השנתי ה-62 למדעי התעופה ו החלל DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: הכנס הישראלי השנתי ה-62  למדעי התעופה ו החלל הוא האירוע השנתי החשוב בלוח השנה של קהילת התעופה והחלל בישראל ומעורר עניין ר ב גם בחו"ל. באירוע לוקחים חלק מהנדסים\, מד ענים ומומחים בתחום האווירונאוטיקה והאסט רונאוטיקה\, המייצגים סוכנויות ותעשיות תע ופה וחלל מקומיות\, כמו גם משתתפים ממרכזי מחקר גדולים ברחבי העולם.\n\n \;\n\n\n Details: \n CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-1227@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230315T013000 DTEND;TZID=Asia/Jerusalem:20230315T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-56@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230315T090000 DTEND;TZID=Asia/Jerusalem:20230316T170000 DTSTAMP:20221030T083459Z URL:https://aerospace.technion.ac.il/events/iacas-62/ SUMMARY:IACAS-62 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: The 62nd Israel Annual Conference on Aerospace Sciences\, spanning sev eral generations\, is an important annual event on the calendar of the aer ospace community in Israel and arouses a great deal of interest abroad. Ta king part in this yearly event are engineers\, scientists\, and experts in the field of aeronautics and astronautics\, representing well-known local aerospace agencies and industries\, as well as participants from major re search centers worldwide.\n\n \;\n\n\n Details: \n CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-1228@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230320T013000 DTEND;TZID=Asia/Jerusalem:20230320T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1229@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230322T013000 DTEND;TZID=Asia/Jerusalem:20230322T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-70@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230323T084500 DTEND;TZID=Asia/Jerusalem:20230323T170000 DTSTAMP:20230320T131047Z URL:https://aerospace.technion.ac.il/events/the-51st-israel-symposium-on-c omputational-mechanics/ SUMMARY:ISCM-51 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n \nאישח"מ - איגוד ישראלי לשיטות ח ישוביות במכניקה\nIACMM – Israel Association for Computatio nal Methods in Mechanics\n******\n \;\n\nThe 51st Israel Symposium on Computational Mechanics (ISCM-51)\n\nDate: Thursday\, March 23rd\, 2023\nV enue: Auditorium 235\, The Faculty of Aerospace Engineering\, Technion.\nK eynote Lecture: Prof. Sanjay Govindjee\, University of California\, Berkel ey\, USA.\nClick here for the ISCM-51 program\n \;\n\n \;\n\nThe s ymposium is supported by the Technion.\n\nLocal organizers: \n\n Dr. Pave l Galich\, faculty of aerospace engineering\, Technion\n Dr. Dana Solav\, faculty of mechanical engineering\, Technion\n\nCommittee:\n\n Dr. Pavel Galich\, faculty of aerospace engineering\, Technion\n Dr. Dana Solav\, faculty of mechanical engineering\, Technion\n Assoc. Prof. Mahmood Jabar een\, faculty of civil engineering\,\nTechnion\n\n \;\n\nOne of the le cturers (excluding the invited lectures) amongst the 50th and 51st symposi a will be\nawarded the association’s support for traveling to an interna tional conference in the\nfield of computational mechanics. CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-71@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230323T084500 DTEND;TZID=Asia/Jerusalem:20230323T174500 DTSTAMP:20230320T130952Z URL:https://aerospace.technion.ac.il/he/events/iscm-51/ SUMMARY:ISCM-51 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n \nאישח"מ - איגוד ישראלי לשיטות ח ישוביות במכניקה\nIACMM – Israel Association for Computatio nal Methods in Mechanics\n******\nThe 51st Israel Symposium on Computation al Mechanics (ISCM-51)\nDate: Thursday\, March 23rd\, 2023\nVenue: Auditor ium 235\, The Faculty of Aerospace Engineering\, Technion.\nKeynote Lectur e: Prof. Sanjay Govindjee\, University of California\, Berkeley\, USA.\n\n \nClick here for the ISCM-51 program\n \;\nThe symposium is supported by the Technion.\nLocal organizers: \n\n\n Dr. Pavel Galich\, faculty of aerospace engineering\, Technion\n Dr. Dana Solav\, faculty of mechanical engineering\, Technion\n\nCommittee:\n\n\n Dr. Pavel Galich\, faculty of aerospace engineering\, Technion\n Dr. Dana Solav\, faculty of mechanica l engineering\, Technion\n Assoc. Prof. Mahmood Jabareen\, faculty of civ il engineering\,\nTechnion\n\nOne of the lecturers (excluding the invited lectures) amongst the 50th and 51st symposia will be\nawarded the associat ion’s support for traveling to an international conference in the\nfield of computational mechanics. CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-1230@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230327T013000 DTEND;TZID=Asia/Jerusalem:20230327T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-196@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230327T133000 DTEND;TZID=Asia/Jerusalem:20230327T143000 DTSTAMP:20230319T135036Z URL:https://aerospace.technion.ac.il/events/distribution-of-families-of-pe riodic-orbits-of-the-hills-problem-and-some-applications-to-space-mission- design/ SUMMARY:Distribution of families of periodic orbits of the Hill’s problem and some applications to space mission design DESCRIPTION:Lecturer:Alexander Batkhin\n Faculty: Singular Problems Departm ent of Keldysh Institute of Applied Mathematics of RAS (KIAM)\, Moscow and Department of Theoretical Mechanics\n Institute:Moscow Institute of Physi cs and Technology (MIPT)\, Dolgoprudny\, Russia.\n Location:Classroom 165\ , ground floor\, Library\, Aerospace Eng\n Zoom: https://technion.zoom.us/ j/99737294922\n Abstract: Hill's variant of the restricted there-body prob lem is one of the most important models in Celestial Mechanics and astrody namics\, with various applications in spacecraft mission design. In this t alk we discuss some statistics of distributions of families of the Hill's problem periodic orbits by symmetry types and by global multiplicities. De scription of singular generating solutions method is provided as well. Eac h generating solution is a finite sequence composed according to certain r ules from a countable set of arcs of two types\, joined at the origin of c oordinates with hyperbolic conics.  Generating solution provides informat ion on symmetry type\, global multiplicity of the orbit and other characte ristics of the corresponding periodic solutions of the generated family. A ccording to obtained statistics it can be possible to state that families of symmetric periodic orbits of the Hill's problem form such a backbone of regular dynamics of the Hill problem. Some applications of obtained resul ts to constructing periodic orbits with prescribed properties are discusse d as well.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-183@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230328T110000 DTEND;TZID=Asia/Jerusalem:20230328T150000 DTSTAMP:20230509T131232Z URL:https://aerospace.technion.ac.il/he/events/%d7%9b%d7%a0%d7%a1-%d7%9e%d 7%97%d7%96%d7%95%d7%a8-%d7%91%d7%95%d7%92%d7%a8%d7%99-1982/ SUMMARY:כנס מחזור - בוגרי 1982 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n מפגש מחזור של בוגרי הנדסת אויר ונוטיקה וחלל 1982.\nבתכנית:\n\n מפגש בוגרים\n פגישה חבר סגל נוכחי\n ארוחת צהרים חגיגית \n\nהאירוע מתקיים בהפקת ארגון בוגרי הטכני ון CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-184@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230328T110000 DTEND;TZID=Asia/Jerusalem:20230328T150000 DTSTAMP:20221213T140559Z URL:https://aerospace.technion.ac.il/events/class-of-1982-alumni-reunion/ SUMMARY:Class of 1982 - Alumni Reunion DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n Reunion of the 1982 Aerospace Engineering graduates.\n\ n Alumni meeting\n Meeting a current faculty member\n Festive lunch\n\n The event is produced by The Technion Alumni Association CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-1231@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230329T013000 DTEND;TZID=Asia/Jerusalem:20230329T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-03-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-195@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230329T133000 DTEND;TZID=Asia/Jerusalem:20230329T143000 DTSTAMP:20230309T100454Z URL:https://aerospace.technion.ac.il/events/plasma-assisted-ammonia-combus tion-experimental-and-modeling-study-of-chemical-kinetics-in-a-well-stirre d-plasma-reactor/ SUMMARY:Plasma Assisted Ammonia Combustion: Experimental And Modeling Study Of Chemical Kinetics In A Well-Stirred Plasma Reactor DESCRIPTION:Lecturer:Galia Faingold\n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng\n Zoom: https://tec hnion.zoom.us/j/97346140543\n Abstract: Abstract: Adaptation of existing i nfrastructure is key for meeting the green-house gas emission targets of t he Paris Climate Accords. Ammonia has broad potential to serve as a carbon -free means of renewable energy storage for mobile applications and power generation\, with energy density and storage costs superior to hydrogen an d existing battery technologies. Its widescale adoption\, however\, has be en limited by its tendency to emit high levels of NOx and its poor combust ion characteristics. Using plasma-assisted reforming\, ammonia can be modi fied to be compatible with current engine technology with only minor alter ations. Plasma chemical processes initiated by high-frequency nanosecond-d uration pulsed energy deposition can dissociate ammonia efficiently and se lectively produce hydrogen and amino radicals\, and when used in conjuncti on with oxidizer\, can also produce nitrous oxide\, among other combustion enhancing species. The presented research will introduce a novel\, well-s tirred plasma reactor for studying the chemistry of ammonia and ammonia-ai r mixtures in a plasma. Gas chromatograph and optical measurements are tak en using this reactor\, measuring hydrogen yields\, oxygen consumption and uniformity of discharge. A chemical kinetic model for ammonia and air in a plasma discharge is constructed and compared to the measurements using a zero-dimensional plasma chemistry solver. Along with ignition simulations \, the measurements and developed kinetic mechanism demonstrate how plasma discharges can enhance ammonia combustion and reduce emissions.\n Details : \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-1232@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230403T013000 DTEND;TZID=Asia/Jerusalem:20230403T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-04-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-197@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230403T133000 DTEND;TZID=Asia/Jerusalem:20230403T143000 DTSTAMP:20230323T073343Z URL:https://aerospace.technion.ac.il/events/optimal-estimation-and-decisio n-in-stochastic-guidance/ SUMMARY:Optimal Estimation and Decision in Stochastic Guidance DESCRIPTION:Lecturer:Liraz Mudrik\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng\n Zoom: https://techn ion.zoom.us/j/91981767571\n Abstract: Perfect-information guidance laws ha ve been known to deliver outstanding performance in simulations complying with their underlying assumptions. However\, as is well known\, realistic guidance of an intercepting missile towards a highly maneuverable target\, using noisy and imperfect measurements\, constitutes a hybrid\, short-hor izon\, nonlinear\, and non-Gaussian stochastic control problem\, and the i mplementation of the guidance law requires an appropriate target state est imator. In such scenarios\, the performance of perfect-information laws ca n degrade gracelessly. We present a novel design paradigm\, which enables the use of perfect-information guidance laws in realistic scenarios by usi ng Bayesian decision theory.\n\nWe first modify the DGL1 guidance law to a ddress estimation errors\, by using Bayesian decision to statistically ran k the costs of all possible guidance decisions. When a unique control cann ot be decided\, this nonuniqueness is harnessed to shape the pursuer's tra jectory to enhance its estimator's performance. We next present an overarc hing tracking and interception strategy\, which is robust against sudden c hanges in the target's evasion maneuver resulting in inevitable estimation  time delays. Whereas the methods presented up to this point follow the s tandard\, miss-distance-minimizing approach\, we next propose an inverse p aradigm whereby\, for a given warhead\, the guidance law maximizes the int erceptor's kill probability against any target. Although the aforementione d methods exhibit significant interception performance improvements\, they are still based on deterministic guidance strategies\, providing no optim ality guarantees. We address this point by presenting a real-time optimal interception strategy for stochastic scenarios based on terminal sets for the linear-Gaussian case with bounded controls.\n\n \;\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-1233@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230405T013000 DTEND;TZID=Asia/Jerusalem:20230405T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-04-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1234@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230410T013000 DTEND;TZID=Asia/Jerusalem:20230410T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-04-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1235@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230412T013000 DTEND;TZID=Asia/Jerusalem:20230412T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-04-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1236@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230417T013000 DTEND;TZID=Asia/Jerusalem:20230417T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-04-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1237@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230419T013000 DTEND;TZID=Asia/Jerusalem:20230419T023000 DTSTAMP:20251118T063916Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-04-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-202@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230419T100000 DTEND;TZID=Asia/Jerusalem:20230419T143000 DTSTAMP:20230328T144814Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%9e%d 7%aa%d7%a2%d7%a0%d7%99%d7%99%d7%a0%d7%99%d7%9d-%d7%91%d7%9c%d7%99%d7%9e%d7 %95%d7%93%d7%99-%d7%aa%d7%95%d7%90%d7%a8-%d7%a8%d7%90%d7%a9%d7%95%d7%9f-%d 7%91%d7%94%d7%a0%d7%93/ SUMMARY:יום מתעניינים בלימודי תואר ראשון בהנ דסת אוירונוטיקה וחלל DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: למי שמחפש את הלימודים הכי גבוהים שיש:\n יום למתעניינים בלימודי תואר ראשון בהנדס ת אוירונוטיקה וחלל.\n\n הרצאת הכרות עם הפק ולטה ומסלולי הלימוד\n חשיפה לתכניות המצו יינות\n הכרות עם המסלול המשולב אווירונאו טיקה-פיזיקה\n הכרות עם סטודנטים בפקולטה ופרוייקטי הסיום\n פגישות עם נציגי מעבדות מחקר וחשיפה לעולמות התוכן בפקולטה\n\nhttps:/ /youtu.be/UgtAF1uEnw8\n\n \;\n\n\n\n \;\n Details: \n CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-198@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230419T130000 DTEND;TZID=Asia/Jerusalem:20230419T143000 DTSTAMP:20230402T090311Z URL:https://aerospace.technion.ac.il/events/israel-pollak-distinguished-le cture-series-lecture-1/ SUMMARY:Israel Pollak Distinguished Lecture Series - Lecture 1 DESCRIPTION:Lecturer:Professor Rodolphe Sepulchre \n Faculty:Department of Engineering\, Division of Information Engineering\, Control group\n Instit ute:Cambridge University\n Location:Auditorium 250\, 2nd floor\, Lady Davi s Building\n Zoom: \n Abstract: Spiking intelligence \n\nSpikes and rhythm s organize control and communication in the animal world\, in contrast to the bits and clocks of digital technology. The invention of the digital co mputer in 1950 put an end to the short-lived cybernetics dream to develop a common language for animal and machine intelligence. Ever since then\, m achine intelligence has focused on computation with digits\, from the firs t computer to the latest generative chatbot. The limitations of this digit al intelligence are now in clear sight\, starting with the unsustainable c arbon footprint of digital technology. The most promising solution to date is the emerging spiking technology of neuromorphic engineering\, initiall y envisioned by Carver Mead in 1990. The talk will describe the current ad vances and challenges of building spiking intelligent machines\, through a control perspective that in many ways can be regarded as a renaissance of the cybernetics dream.\n\n \;\n\n\n Details: \n CATEGORIES:Events LOCATION:Auditorium 250\, 2nd floor\, Lady Davis Building END:VEVENT BEGIN:VEVENT UID:0-199@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230419T130000 DTEND;TZID=Asia/Jerusalem:20230419T143000 DTSTAMP:20230402T085821Z URL:https://aerospace.technion.ac.il/he/events/%d7%a1%d7%93%d7%a8%d7%aa-%d 7%94%d7%a8%d7%a6%d7%90%d7%95%d7%aa-%d7%90%d7%95%d7%a8%d7%97-%d7%a2%d7%a9-% d7%99%d7%a9%d7%a8%d7%90%d7%9c-%d7%a4%d7%95%d7%9c%d7%a7-%d7%94%d7%a8%d7%a6% d7%90%d7%94-1/ SUMMARY:סדרת הרצאות אורח ע"ש ישראל פולק - הרצא ה 1 DESCRIPTION:Lecturer:Professor Rodolphe Sepulchre \n Faculty:Department of Engineering\, Division of Information Engineering\, Control group\n Instit ute:Cambridge University\n Location:אודיטוריום 250 \, קומה 2 בניין ליידי דוויס\n Zoom: \n Abstract: Spikes and rhythms organize control and communication in the animal world\, in contrast to th e bits and clocks of digital technology. The invention of the digital comp uter in 1950 put an end to the short-lived cybernetics dream to develop a common language for animal and machine intelligence. Ever since then\, mac hine intelligence has focused on computation with digits\, from the first computer to the latest generative chatbot. The limitations of this digital intelligence are now in clear sight\, starting with the unsustainable car bon footprint of digital technology. The most promising solution to date i s the emerging spiking technology of neuromorphic engineering\, initially envisioned by Carver Mead in 1990. The talk will describe the current adva nces and challenges of building spiking intelligent machines\, through a c ontrol perspective that in many ways can be regarded as a renaissance of t he cybernetics dream.\n\n Details: \n CATEGORIES:אירועים LOCATION:אודיטוריום 250 \, קומה 2 בניין ליידי דו ויס END:VEVENT BEGIN:VEVENT UID:0-223@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230419T133000 DTEND;TZID=Asia/Jerusalem:20230419T143000 DTSTAMP:20230416T103900Z URL:https://aerospace.technion.ac.il/events/shape-development-and-stabilit y-of-a-supercavitation-bubble/ SUMMARY:Shape\, Development and Stability of a Supercavitation Bubble DESCRIPTION:Lecturer:Lotan Arad Ludar\n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Meeting Room 203 - Rocket Propulsion Center\n Zoom: https://technion.zoo m.us/j/97346140543\n Abstract: The Supercavitation phenomenon has been stu died for decades utilizing the nature vaporization of the water surroundin g high speed underwater vehicles to reduce the drag acting on the supercav itational bodies. Yet\, many questions and problems remained open and unso lved regarding the process and the characteristics of the bubble and the s upercavitational regime. Understanding the creation and development\, the shape\, and the stability of a supercavitation bubble is essential for the design of supercavitational underwater vehicles and applications and it i s at the center of this study.\n\nTo enhance understanding of the supercav itation bubble shape and structure\, two series of experiments have been c onducted in two advanced systems: one resemble a duct flow\, and the other a free-surface flow. The experiments have been applied on cylindrical sle nder bodies in a uniform flow of water\, in different flow speeds. A compa rison of supercavitation bubbles created on bodies with different nose geo metries (i.e.\, cavitators)\, has been made. The comparison was referred t o the conditions of the bubbles’ creation and collapse\, and also their shape and development.\n\nAlso theoretical efforts have been made\, in ord er to examine the supercavitation bubble geometry. An analytical model of an axisymmetric supercavitation bubble in a viscous flow has been made.  The viscosity of the flow has typically been neglected in research on supe rcavitational flows\, using non-viscous potential flows. However\, for som e situations and conditions\, the viscosity was found to be significant an d crucial for the bubble geometry and formation\, especially at the superc avitation bubble detachment point. The results of the analyses show the ch ange of the bubble formation from past models due to the viscosity\, and o ffer a more accurate description of the bubble geometry.\n\nAnother theore tical examination conducted in this study\, aimed at learning about the pr essure field of the supercavitation bubble. Actually\, the underwater vess el is surrounded by an inhomogeneous fluid containing cavities (also descr ibed as microbubbles). The distribution of the cavities in the supercavita tion volume dictates the pressure field and thus determines the stresses a nd forces that act on the vessel and affect its motion and stability. In t his research\, we suggest a new approach to studying the bubbles’ format ion and learning about the cavities’ distribution in the low-pressure vo lume using a stochastic model\, describing the random movement of the cavi ties.\n Details: \n CATEGORIES:Seminars LOCATION:Meeting Room 203 - Rocket Propulsion Center END:VEVENT BEGIN:VEVENT UID:0-200@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230420T140000 DTEND;TZID=Asia/Jerusalem:20230420T153000 DTSTAMP:20230402T090105Z URL:https://aerospace.technion.ac.il/events/israel-pollak-distinguished-le cture-series-lecture-2/ SUMMARY:Israel Pollak Distinguished Lecture Series – Lecture 2 DESCRIPTION:Lecturer:Professor Rodolphe Sepulchre \n Faculty:Department of Engineering\, Division of Information Engineering\, Control group\n Instit ute:Cambridge University\n Location:Auditorium 235 - Department of Aerospa ce Engineering\n Zoom: \n Abstract: "To know or to predict? 70 years of Ho dgkin-Huxley modelling in science and engineering"\n\nLove them or hate th em\, the equations of Hodgkin and Huxley remain in 2022 a seemingly inesca pable biophysical entry point to understanding the dynamical and rhythmic nature of brain activity. For 70 years\, they have defined a unique encoun ter point between physiology and circuit theory\, between science and engi neering. This talk by a control theorist will tell the story of a personal journey of working with this unique model. A journey from intractable non linear differential equations to an enligthening mixed-feedback principle unfold by two neurophysiologists once exposed to control engineering by th e necessity of war.\n\n \;\n\n\n Details: \n CATEGORIES:Events LOCATION:Auditorium 235 - Department of Aerospace Engineering END:VEVENT BEGIN:VEVENT UID:0-201@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230420T140000 DTEND;TZID=Asia/Jerusalem:20230420T153000 DTSTAMP:20230402T090141Z URL:https://aerospace.technion.ac.il/he/events/%d7%a1%d7%93%d7%a8%d7%aa-%d 7%94%d7%a8%d7%a6%d7%90%d7%95%d7%aa-%d7%90%d7%95%d7%a8%d7%97-%d7%a2%d7%a9-% d7%99%d7%a9%d7%a8%d7%90%d7%9c-%d7%a4%d7%95%d7%9c%d7%a7-%d7%94%d7%a8%d7%a6% d7%90%d7%94-2/ SUMMARY:סדרת הרצאות אורח ע"ש ישראל פולק - הרצא ה 2 DESCRIPTION:Lecturer:Professor Rodolphe Sepulchre \n Faculty:Department of Engineering\, Division of Information Engineering\, Control group\n Instit ute:Cambridge University\n Location:אודיטוריום 235 - הפקול טה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: "To know or to predict? 70 years of Hodgkin-Huxley modelling in science and e ngineering"\nLove them or hate them\, the equations of Hodgkin and Huxley remain in 2022 a seemingly inescapable biophysical entry point to understa nding the dynamical and rhythmic nature of brain activity. For 70 years\, they have defined a unique encounter point between physiology and circuit theory\, between science and engineering. This talk by a control theorist will tell the story of a personal journey of working with this unique mode l. A journey from intractable nonlinear differential equations to an enlig thening mixed-feedback principle unfold by two neurophysiologists once exp osed to control engineering by the necessity of war.\n\n\n Details: \n CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1238@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230424T013000 DTEND;TZID=Asia/Jerusalem:20230424T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-04-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1239@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230426T013000 DTEND;TZID=Asia/Jerusalem:20230426T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-04-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1240@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230501T013000 DTEND;TZID=Asia/Jerusalem:20230501T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1241@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230503T013000 DTEND;TZID=Asia/Jerusalem:20230503T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-243@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230503T123000 DTEND;TZID=Asia/Jerusalem:20230503T140000 DTSTAMP:20230501T063718Z URL:https://aerospace.technion.ac.il/events/uri-oron-lecture/ SUMMARY:Israeli Space Agency (ISA) DESCRIPTION:Lecturer:Brigadier General (Res.) Uri Oron\n Faculty:\n Institu te:Israel Aerospace Agency in the Ministry of Innovation\, Science and Tec hnology\n Location:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: The Israel Space Agency\, founded following a government decision in 1983\, is a national agency operating under the auspices of the Ministry of Science and Technology. The Agency is responsi ble for initiating\, leading and coordinating all activities of the civili an space program.\n\nThe Agency especially supports scientific research an d development with real\, economic potential such as the development of un ique and innovative technologies. In addition\, the Agency operates on the premise that all space related activities contribute to the Israeli econo my\, to the country’s international standing and also benefit its citize ns in terms of agriculture\, communications\, monitoring of environmental pollution and research.\n\nRead more at: https://www.space.gov.il/en/resea rch-and-development\n\n \;\n Details: \n CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-244@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230503T123000 DTEND;TZID=Asia/Jerusalem:20230503T140000 DTSTAMP:20230501T064810Z URL:https://aerospace.technion.ac.il/he/events/%d7%a1%d7%95%d7%9b%d7%a0%d7 %95%d7%aa-%d7%94%d7%97%d7%9c%d7%9c-%d7%94%d7%99%d7%a9%d7%a8%d7%90%d7%9c%d7 %99%d7%aa-isa/ SUMMARY:סוכנות החלל הישראלית (ISA) DESCRIPTION:Lecturer:תא"ל (מיל) אורי אורון\n Faculty:\n Inst itute:סוכנות החלל הישראלית\, משרד החדשנות\, המדע והטכנולוגיה\n Location:אודיטוריום 235 - ה פקולטה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstr act: סוכנות החלל הישראלית היא גוף ממלכתי ה פועל במסגרת משרד החדשנות\, המדע והטכנולו גיה. הסוכנות יוזמת\, מובילה ומתאמת את פעי לות החלל האזרחית בישראל.\n\nהסוכנות תומכת במיוחד במחקר ופיתוח מדעי בעלי פוטנציאל כ לכלי ממשי\, כגון פיתוח טכנולוגיות ייחודי ות וחדשניות. כמו כן\, הסוכנות פועלת מתוך ת פיסה כי העיסוק בחלל תורם לכלכלת ישראל\, ל מיצוב מעמדה בעולם ולרווחת התושבים בהיבט ים של חקלאות\, תקשורת\, ניטור זיהומים סביב תיים ומחקר.\n\nיעדי סוכנות החלל הישראלית ה ם רבים ומגוונים\, ביניהם ניתן למנות את הר חבת שיתוף הפעולה ויחסי הגומלין עם מדינות שונות בתחום החלל\, קידום מחקרי תשתית באק דמיה ובמכוני המחקר\; השקעה בחברות סטרטאפ המפתחות רכיבים שונים לתעשיות החלל בארץ ו בעולם\; פיתוח ובניית לוויינים למטרות אזר חיות ותמיכה בפיתוח טכנולוגיות חלל חדשני ות וייחודיות בתעשיות החלל\; וכן טיפוח עתו דת מדעני העתיד בתחום חקר החלל דרך חינוך ל חלל ופרויקטים בקהילה\, ובאופן כללי הרחבת היתרון היחסי של ישראל בתחום והצבתה בין ה מדינות המובילות בעולם בחקר החלל ובניצול ו.\nקראו עוד על אודות פעילות סוכנות החלל ה ישראלית במחקר ופיתוח מקומיים ושיתופי פע ולה בינלאומיים.\n Details: \n CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-242@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230503T133000 DTEND;TZID=Asia/Jerusalem:20230503T143000 DTSTAMP:20230508T073841Z URL:https://aerospace.technion.ac.il/events/optimization-of-a-hybrid-rocke t-motor-with-a-volume-limited-fuel-grain/ SUMMARY:Optimization of a Hybrid Rocket Motor with a Volume-Limited Fuel Gr ain DESCRIPTION:Lecturer:Michael Presman\n Faculty:Department of Aerospace Engi neering\n Institute:Technion – Israel Institute of Technology\n Location :Classroom 165\, ground floor\, Library\, Aerospace Eng\n Zoom: https://te chnion.zoom.us/j/97346140543\n Abstract: Hybrid rocket propulsion is a pro mising compromise between the solid and liquid types\, that has not fully matured yet mainly due to industry conservatism. The purpose of this work was evaluation of different optimization aspects related to a hybrid syste m containing a volume-limited fuel grain. Thermochemical calculations were performed to find the “best” oxidizer-fuel combination. The H2O2-Poly ester combination showed the most promising results (in ρˑIsp) for volum e-limited systems. An optimization scheme based on a genetic algorithm was formulated\, developed\, and implemented in MATLAB to support the effort of optimizing the whole motor for a specific mission (the Goddard Problem) . Three grain types were used as test cases to demonstrate the ability: th e Central Cylindrical Port\, the Wagon Wheel\, and the “Jagged Star”. The “Jagged Star” type showed the most promising results\, but only by a small difference (-6% in cost function value) from more conventional de signs. Improvement in the models used and manufacturing capabilities (such as Additive Manufacturing) are key to realize optimized designs.\n Detail s: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-1242@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230508T013000 DTEND;TZID=Asia/Jerusalem:20230508T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1243@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230510T013000 DTEND;TZID=Asia/Jerusalem:20230510T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-246@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230510T123000 DTEND;TZID=Asia/Jerusalem:20230510T134500 DTSTAMP:20230509T091036Z URL:https://aerospace.technion.ac.il/he/events/%d7%a7%d7%95%d7%a0%d7%a6%d7 %a8%d7%98-%d7%a4%d7%a7%d7%95%d7%9c%d7%98%d7%99/ SUMMARY:קונצרט פקולטי DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:אודיטור יום 235 - הפקולטה להנדסת אוירונוטיקה וחלל\ n Zoom: \n Abstract: חברי סגל וסטודנטים מוכשרים י נגנו וישירו בקונצרט הפקולטי השנתי הרביע י. מנחה האירוע (וגם ינגן בו) פרופ"ח אבשלום מנלה.\n\nהתכנסות ב 12:30 לפיצה ובירה בפיטריי ה וב 13:00 כניסה לאודיטוריום.\n\n\n\n \;\n Details: \n CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-245@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230510T123000 DTEND;TZID=Asia/Jerusalem:20230510T134500 DTSTAMP:20230501T144318Z URL:https://aerospace.technion.ac.il/events/faculty-concert/ SUMMARY:Faculty Concert DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Auditorium 235 \, The Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: AE Rocks! Talented faculty members and students will play and sing at the 4t h Annual Faculty Concert.\n Details: \n CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1244@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230515T013000 DTEND;TZID=Asia/Jerusalem:20230515T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1245@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230517T013000 DTEND;TZID=Asia/Jerusalem:20230517T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1246@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230522T013000 DTEND;TZID=Asia/Jerusalem:20230522T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1247@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230524T013000 DTEND;TZID=Asia/Jerusalem:20230524T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-254@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230524T133000 DTEND;TZID=Asia/Jerusalem:20230524T143000 DTSTAMP:20230517T141636Z URL:https://aerospace.technion.ac.il/events/empowering-uav-autonomy-throug h-innovative-guidance-design/ SUMMARY:Empowering UAV Autonomy Through Innovative Guidance Design DESCRIPTION:Lecturer:Prof. Ashwini Ratnoo\n Faculty:Department of Aerospace Engineering\n Institute:Indian Institute of Science\, Bengaluru-560012\, India\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/97346140543\n Abstract: UAVs are desired to autonomously execute increasingly complex mission scenarios.  Hand ling a set of different tasks typically involves different guidance method s and associated sensory requirements. In this talk we will focus on the q uest for finding a guidance architecture that offers greater diversity in UAV trajectories. Specifically\, we investigate bifurcation-based guidance design wherein change in design parameter(s) changes the system topology. An example scenario is discussed wherein Pitchfork Bifurcation is used to generate a diverse set of target tracking and surveillance trajectories. Relying essentially on the same measurements\, bifurcation-based guidance design paves way for greater autonomy without additional information or co mplexities.\n\n \;\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1248@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230529T013000 DTEND;TZID=Asia/Jerusalem:20230529T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-251@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230529T133000 DTEND;TZID=Asia/Jerusalem:20230529T143000 DTSTAMP:20230517T112045Z URL:https://aerospace.technion.ac.il/events/laminar-to-turbulent-transitio n-in-airfoil-boundary-layer-flows-at-unsteady-inflow-conditions/ SUMMARY:Laminar-to-turbulent transition in airfoil boundary-layer flows at unsteady inflow conditions DESCRIPTION:Lecturer:Duncan Ohno\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://techn ion.zoom.us/j/97346140543\n Abstract: The presented work was performed at the boundary-layers group of the Institute of Aerodynamics and Gas Dynamic s\, Stuttgart:\n\nLaminar-to-turbulent transition in boundary-layer flows on natural laminar flow (NLF) airfoils under oscillating inflow conditions is numerically investigated. In the cases studied\, large-scale fluctuati ons in the form of periodic vertical gusts generate an oscillating pressur e gradient which results in a complex transient behavior of the boundary l ayer. Under these conditions\, two scenarios are investigated: an attached flow with natural Tollmien-Schlichting (TS) wave transition and a boundar y-layer flow featuring a laminar separation bubble (LSB). The study aims t o provide an in-depth understanding of the transient mechanisms as well as the basis for new transition prediction methods at unsteady conditions.\n \nDirect numerical simulations (DNS) are performed where the gust disturba nce is imposed on the fully-resolved transitional boundary layers via unst eady boundary conditions. In this novel (hybrid) approach\, transient base flows are generated in advance with unsteady Reynolds-averaged Navier-Sto kes (URANS) simulations of entire unsteady airfoil flows in conjunction wi th the so-called disturbance velocity approach (DVA) to introduce sinusoid al gusts. The spatio-temporal evolution of the modal disturbances is analy zed using the continuous wavelet transform (CWT)\, which is then compared with linear stability theory (LST) by employing a trajectory-following met hod developed for transient flows. The numerical methods are validated wit h experimental results.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-252@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230529T170000 DTEND;TZID=Asia/Jerusalem:20230529T183000 DTSTAMP:20230517T093904Z URL:https://aerospace.technion.ac.il/events/aerospace-phd-graduation/ SUMMARY:Aerospace PhD graduation DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Graduate Stude nts Lounge\n Zoom: \n Abstract: \n Details: \n CATEGORIES:Events LOCATION:Graduate Students Lounge END:VEVENT BEGIN:VEVENT UID:0-253@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230529T170000 DTEND;TZID=Asia/Jerusalem:20230529T183000 DTSTAMP:20230517T093653Z URL:https://aerospace.technion.ac.il/he/events/%d7%a7%d7%91%d7%9c%d7%aa-%d 7%a4%d7%a0%d7%99%d7%9d-%d7%9c%d7%93%d7%95%d7%a7%d7%98%d7%95%d7%a8%d7%a0%d7 %98%d7%99%d7%9d-%d7%94%d7%9e%d7%a1%d7%99%d7%99%d7%9e%d7%99%d7%9d/ SUMMARY:קבלת פנים לדוקטורנטים המסיימים DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:הטכניון - מכון טכנולוגי לישראל\n Location:Graduate Students Lounge\n Zoom: \n Abstract: \n D etails: \n באווירה משפחתית נתכנס יחד\, מקבלי ת ואר דוקטור מהפקולטה להנדסת אוירונוטיקה וחלל\, חברי הסגל המנחים ובני משפחת המסיימ ים\, לאירוע הרמת כוסית חגיגית וברכת הפקול טה למסיימים. CATEGORIES:אירועים LOCATION:Graduate Students Lounge END:VEVENT BEGIN:VEVENT UID:0-1249@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230531T013000 DTEND;TZID=Asia/Jerusalem:20230531T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-05-31/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1250@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230605T013000 DTEND;TZID=Asia/Jerusalem:20230605T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-06-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-248@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230605T133000 DTEND;TZID=Asia/Jerusalem:20230605T143000 DTSTAMP:20230605T073121Z URL:https://aerospace.technion.ac.il/events/on-the-use-of-supersonic-jet-c urtains-for-control-of-moments-on-tailless-aircraft/ SUMMARY:On The Use of Supersonic Jet-Curtains for Control of Moments on Tai lless Aircraft DESCRIPTION:Lecturer:Prof. Israel Wygnanski\n Faculty:AME Department \n Ins titute:The University of Arizona. Also\, Professor Emeritus Tel Aviv Unive rsity\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/97346140543\n Abstract: The purpose of t his study was to explore the replacement of conventional moving control su rfaces on a typical tailless aircraft model at high subsonic cruise speeds . Since the efficacy of sweeping jet actuators was only demonstrated at lo w speeds\, the current test considered their potential replacement by Supe rsonic Steady Jets (SSJs) of identical nozzle dimensions. It was shown tha t even a single SSJ properly located and appropriately oriented may outper form an array of actuators whose location and orientation did not take int o consideration the changing local flow conditions. The test article chose n was the SWIFT model that represents a typical blended wing-body configur ation of a tailless aircraft. It was selected because it was tested extens ively using Sweeping Jet Actuators (SJAs) that could be used for compariso n. When a single supersonic jet designed for Mn=1.5 was used to control th e pitch it was able to increase the trimmed lift almost as well as an arra y of SJAs while providing a much better yaw control at small accompanying rolling moment. These tests proved that the momentum input is but one of m any parameters controlling the flow and they demonstrated the richness of the parameter space involved in AFC design even after the wing design was frozen\n\n\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1251@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230607T013000 DTEND;TZID=Asia/Jerusalem:20230607T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-06-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1252@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230612T013000 DTEND;TZID=Asia/Jerusalem:20230612T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-06-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1253@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230614T013000 DTEND;TZID=Asia/Jerusalem:20230614T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-06-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-203@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230614T123000 DTEND;TZID=Asia/Jerusalem:20230614T143000 DTSTAMP:20230501T093135Z URL:https://aerospace.technion.ac.il/events/research-day-2023/ SUMMARY:Research Day 2023 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Faculty of Aerospa ce Engineering\n Zoom: \n Abstract: Our Graduate Studies Research Day is a n annual event that attracts not only Aerospace Engineering students and f aculty members but also students from around the campus as well as aerospa ce professionals from the industry. The graduate students presented their research posters to the audience.\n\nAs part of the tradition\, a judging committee chose the best posters of M.Sc. students and Ph.D. students. In addition\, the crowd picked its favorite.\n\n\n Details: \n CATEGORIES:Events LOCATION:Faculty of Aerospace Engineering END:VEVENT BEGIN:VEVENT UID:0-204@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230614T123000 DTEND;TZID=Asia/Jerusalem:20230614T143000 DTSTAMP:20230501T093216Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%94%d 7%9e%d7%97%d7%a7%d7%a8-2023/ SUMMARY:יום המחקר 2023 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:מדשאת הפק ולטה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: יום המחקר הפקולטי לתארים מתקדמים הוא אי רוע שנתי שמושך לא רק סטודנטים וחברי סגל ל הנדסת אוירונוטיקה וחלל\, אלא גם סטודנטים מרחבי הקמפוס\, כמו גם אנשי מקצוע בתחום הת עופה והחלל מהתעשייה. הסטודנטים לתוארים ש ני ודוקטורט מציגים את פרי המחקרים שלהם ל קהל באירוע הפנינג שנתי גדול.\n\nכחלק מהמסו רת\, ועדת שיפוט בוחרת את המחקרים הנבחרים. בנוסף\, הקהל מצביע ובוחר את המחקר חביב הק הל.\n\n\n Details: \n CATEGORIES:אירועים LOCATION:מדשאת הפקולטה להנדסת אוירונוטיקה וח לל END:VEVENT BEGIN:VEVENT UID:0-1254@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230619T013000 DTEND;TZID=Asia/Jerusalem:20230619T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-06-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1255@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230621T013000 DTEND;TZID=Asia/Jerusalem:20230621T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-06-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1256@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230626T013000 DTEND;TZID=Asia/Jerusalem:20230626T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-06-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-440@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230626T133000 DTEND;TZID=Asia/Jerusalem:20230626T143000 DTSTAMP:20230531T084144Z URL:https://aerospace.technion.ac.il/events/optimal-trajectory-for-a-hyper sonic-scramjet-missile-with-a-non-convex-control-set/ SUMMARY:Optimal Trajectory for a Hypersonic Scramjet Missile with a Non-Con vex Control Set DESCRIPTION:Lecturer:Sahar Shachar \n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://te chnion.zoom.us/j/97346140543\n Abstract: Optimal control problems (OCPs) h ave wide-ranging applications across various industries\, including aerosp ace technologies. Currently\, there is significant interest in Hypersonic Cruise Missiles (HCMs) as cutting-edge weapons developed by major military powers. This study focuses on solving the maximum range OCP for such a mi ssile. The chosen controls are the angle-of-attack (AOA) and fuel flow of the Scramjet engine. This research is the first to address the maximum ran ge problem with a unique relationship between the controls\, allowing the engine to make decisions regarding activation or deactivation. When the en gine is activated\, the AOA must be limited due to engine limitations\, bu t when deactivated\, a larger AOA is enabled.\n\nThe suggested relation is expressed as Vanishing Constraints\, where the control set becomes non-co nvex\, and the linear independent constraint qualification is failing\, ma king it challenging to solve. To overcome this problem\, we present a modi fied variable time transformation (VTT) method to deal numerically with th ese problems.\n\nThe HCM problem with the suggested relation was solved us ing the VTT and by directly implementing the OCP into existing optimizatio n software. Both methods yielded very similar trajectories\, confirming th e VTT’s validity. All the problems were solved numerically using the FAL CON optimization tool.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1257@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230628T013000 DTEND;TZID=Asia/Jerusalem:20230628T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-06-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1258@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230703T013000 DTEND;TZID=Asia/Jerusalem:20230703T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1259@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230705T013000 DTEND;TZID=Asia/Jerusalem:20230705T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1260@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230710T013000 DTEND;TZID=Asia/Jerusalem:20230710T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1261@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230712T013000 DTEND;TZID=Asia/Jerusalem:20230712T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1262@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230717T013000 DTEND;TZID=Asia/Jerusalem:20230717T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1263@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230719T013000 DTEND;TZID=Asia/Jerusalem:20230719T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1264@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230724T013000 DTEND;TZID=Asia/Jerusalem:20230724T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1265@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230726T013000 DTEND;TZID=Asia/Jerusalem:20230726T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1266@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230731T013000 DTEND;TZID=Asia/Jerusalem:20230731T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-07-31/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1267@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230802T013000 DTEND;TZID=Asia/Jerusalem:20230802T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1268@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230807T013000 DTEND;TZID=Asia/Jerusalem:20230807T023000 DTSTAMP:20251118T063915Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1269@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230809T013000 DTEND;TZID=Asia/Jerusalem:20230809T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1270@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230814T013000 DTEND;TZID=Asia/Jerusalem:20230814T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-543@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230814T133000 DTEND;TZID=Asia/Jerusalem:20230814T143000 DTSTAMP:20230727T070737Z URL:https://aerospace.technion.ac.il/events/realizable-high-order-methods- for-non-equilibrium-multi-physics-flows/ SUMMARY:Realizable High-Order Methods for Non-Equilibrium\, Multi-Physics F lows DESCRIPTION:Lecturer:Sahar Shpitz \n Faculty:Department of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:C lassroom 165\, ground floor\, Library\, Aerospace Eng\n Zoom: https://tech nion.zoom.us/j/97346140543\n Abstract: \n\n\nMost real-life flows are mult i-physics\, meaning that they encompass several different physical phenome na\, in addition to the mechanism of the basic flow. Numerically solving m ulti-physics problems is not trivial. The major desired properties of any numerical scheme are accuracy\, efficiency\, and realizability.\n\nIn this study\, we focus on accuracy and efficiency\, and introduce\, analyze\, a nd apply a novel semi-discrete numerical approach for solving conservation equations\, applicable to both reactive and non-reactive fluid flows acro ss a variety of one-dimensional problems. Commonly\, literature refers to semi-discrete methods as discretization schemes that discretize spatial de rivatives while leaving the temporal derivative continuous. These methodol ogies often include the method of lines or exponential integrator methods. The resulting system of ordinary differential equations (ODEs) is then so lved using a time marching method.\n\nOur innovative approach discretizes the temporal derivative\, leaving the spatial derivatives continuous. Subs equently\, the ODE is solved analytically in the local region surrounding each finite difference mesh point\, resulting in a set of algebraic tridia gonal equations that can be straightforwardly solved numerically. The prim ary advantage of this method is the attainment of high spatial accuracy wi th minimal computational cost.\n\nWe will present this new method in compr ehensive detail\, utilizing various discretization methods for the tempora l derivative\, and analyzing it in terms of stability and the order of con vergence. We will then apply it to a variety of problems\, including syste ms of coupled Burgers' equations and reactive advection-diffusion equation s.\n\n\n\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-1271@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230816T013000 DTEND;TZID=Asia/Jerusalem:20230816T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1272@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230821T013000 DTEND;TZID=Asia/Jerusalem:20230821T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1273@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230823T013000 DTEND;TZID=Asia/Jerusalem:20230823T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1274@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230828T013000 DTEND;TZID=Asia/Jerusalem:20230828T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-544@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230828T133000 DTEND;TZID=Asia/Jerusalem:20230828T143000 DTSTAMP:20230828T112015Z URL:https://aerospace.technion.ac.il/events/the-bridge-between-optimizatio n-and-simulation-applications-to-atm/ SUMMARY:The Bridge Between Optimization and Simulation: Applications to ATM DESCRIPTION:Lecturer:Prof. Daniel Delahaye \n Faculty:Head of Optimization and Machine Learning Team\n Institute:ENAC : French Civil Aviation Univers ity\, Toulouse\, France\n Location:\n Zoom: https://technion.zoom.us/j/973 46140543\n Abstract: The talk will start with a brief overview of the opti mization methods and machine learning (ML) algorithms\, focusing on the ob jective function evaluation. The benefit obtained by connecting optimizati on and simulation will then be addressed. Such an optimization-simulation approach can be also improved by the mean of machine learning. Application s to air traffic management operations will then be presented\, covering t rajectory planning\, automatic sector design\, SID-STAR automatic design\, emergency trajectory design\, AMAN-SMAN-DMAN integration at CDG\, and mor e.\n Details: \n CATEGORIES:Seminars END:VEVENT BEGIN:VEVENT UID:0-1275@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230830T013000 DTEND;TZID=Asia/Jerusalem:20230830T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-08-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1276@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230904T013000 DTEND;TZID=Asia/Jerusalem:20230904T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-09-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-249@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230904T100000 DTEND;TZID=Asia/Jerusalem:20230904T161500 DTSTAMP:20230509T130915Z URL:https://aerospace.technion.ac.il/events/class-of-1972-alumni-reunion/ SUMMARY:Class of 1972 – Alumni Reunion DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Classroom 165\ , ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n Reunion of the 1972 Aerospace Engineering graduates.\n\n Alumni meeti ng\n Meeting a current faculty member\n Festive lunch\n\nThe event is pr oduced by The Technion Alumni Association\n\n ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2023/01/1972-HD-scaled.jpg CATEGORIES:Events LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-250@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230904T100000 DTEND;TZID=Asia/Jerusalem:20230904T160000 DTSTAMP:20230509T131240Z URL:https://aerospace.technion.ac.il/he/events/%d7%9b%d7%a0%d7%a1-%d7%9e%d 7%97%d7%96%d7%95%d7%a8-%d7%91%d7%95%d7%92%d7%a8%d7%99-1972/ SUMMARY:כנס מחזור - בוגרי 1972 DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:הטכניון - מכון טכנולוגי לישראל\n Location:כיתת הספרייה 165\, הפקולטה לה נדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: \n Details: \n מפגש מחזור של בוגרי הנדסת אוירונוטיקה וחלל 1982.\nבתכנית:\n\n מפגש בוגרים\n פגישה ח בר סגל נוכחי\n ארוחת צהרים חגיגית\n\nהאירו ע מתקיים בהפקת ארגון בוגרי הטכניון\n\n ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2023/01/1972-HD-scaled.jpg CATEGORIES:אירועים LOCATION:כיתת הספרייה 165\, הפקולטה להנדסת אויר ונוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1277@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230906T013000 DTEND;TZID=Asia/Jerusalem:20230906T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-09-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-545@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230906T090000 DTEND;TZID=Asia/Jerusalem:20230906T173000 DTSTAMP:20230802T081842Z URL:https://aerospace.technion.ac.il/events/the-first-israeli-conference-f or-applied-rocket-propulsion/ SUMMARY:The First Israeli Conference For Applied Rocket Propulsion DESCRIPTION:Lecturer:\n Faculty:\n Institute:Technion – Israel Institute of Technology\n Location:Electrical &\; Computer Engineering\, Meyer Bu ilding\n Zoom: \n Abstract: The Applied Rocket Propulsion Conference welco mes engineers and researchers from academia and industry who are invited t o present\, be exposed to\, and discuss research on a variety of topics re lated to rocket propulsion systems\, such as solid propellants\, liquid pr opulsion\, new propulsion technologies\, guidance systems\, design\, produ ction\, and system engineering.\n\nThe conference will be held with the pa rticipation of academia\, industries\, and the Ministry of Defense and wil l include several plenary lectures\, an expert panel\, and parallel sessio ns of lectures and discussion panels.\n\nThe conference is mainly relevant for aeronautics and space engineers\, mechanics\, chemistry\, physicists\ , and chemists in propulsion\, structure\, flow\, simulation\, combustion\ , flight mechanics\, project management\, production\, and quality assuran ce.\n\nClick here for the conference website\n\nThe conference will be hel d in Hebrew.\n Details: \n CATEGORIES:Events LOCATION:Electrical &\; Computer Engineering\, Meyer Building END:VEVENT BEGIN:VEVENT UID:0-546@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230906T090000 DTEND;TZID=Asia/Jerusalem:20230906T173000 DTSTAMP:20230802T082602Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%9b%d7%a0%d7%a1-%d 7%94%d7%99%d7%a9%d7%a8%d7%90%d7%9c%d7%99-%d7%94%d7%a8%d7%90%d7%a9%d7%95%d7 %9f-%d7%9c%d7%94%d7%a0%d7%a2%d7%94-%d7%a8%d7%a7%d7%98%d7%99%d7%aa-%d7%99%d 7%99%d7%a9%d7%95%d7%9e/ SUMMARY:הכנס הישראלי הראשון להנעה רקטית יישו מית DESCRIPTION:Lecturer:\n Faculty:\n Institute:הטכניון - מכון טכ נולוגי לישראל\n Location:בניין מאייר\, הפקולט ה להנדסת חשמל ומחשבים\n Zoom: \n Abstract: כנס הנע ה רקטית יישומית מיועד למהנדסים וחוקרים מ האקדמיה והתעשייה המוזמנים להציג\, להיחשף ולדון במחקר במגוון נושאים הנוגעים למערכ ות הנעה רקטית כגון הודפים מוצקים\, הנעה נ וזלית\, טכנולוגיות הנעה חדשות\, מערכות הכ וון\, תכן\, ייצור והנדסת מערכת.\n\nהכנס יערך בהשתתפות האקדמיה\, התעשיות ומשרד הבטחון יכלול מספר הרצאות מליאה\, פאנל מומחים\, וכ ן מספר מושבים מקבילים של הרצאות ופאנלים.\ n\nהכנס מיועד למהנדסי אווירונאוטיקה וחלל\ , מכונות\, כימיה\, פיסיקאים וכימאים העוסקי ם בתחומי ההנעה\, מבנה\, זרימה\, סימולציה\, ב עירה\, מכניקת טיס\, ניהול פרויקטים\, ייצור ואבטחת איכות.\n\nהכנס יתנהל בשפה העברית.\n\n קישור לאתר ולתוכנית הכנס\n Details: \n CATEGORIES:אירועים LOCATION:בניין מאייר\, הפקולטה להנדסת חשמל ומ חשבים END:VEVENT BEGIN:VEVENT UID:0-542@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230906T133000 DTEND;TZID=Asia/Jerusalem:20230906T143000 DTSTAMP:20230725T063710Z URL:https://aerospace.technion.ac.il/events/towards-abatement-of-quadrotor s-acoustic-signature-with-phase-control-technology/ SUMMARY:Towards Abatement of Quadrotor’s Acoustic Signature with Phase Co ntrol Technology DESCRIPTION:Lecturer:Ofek Hertzman \n Faculty:Department of Aerospace Engin eering\n Institute:Technion – Israel Institute of Technology\n Location: Classroom 165\, ground floor\, Library\, Aerospace Eng\n Zoom: https://tec hnion.zoom.us/j/97346140543\n Abstract: The annoying sound produced by a m ulti-rotor vehicle can bring a severe acoustic nuisance to an urban sounds cape. Hence\, it is paramount to find a solution to attenuate the acoustic signature of a multi-rotor platform for further public development and ac ceptance of these vehicles. In the scope of the MSc thesis\, a phase contr ol technique was applied to attenuate acoustic signature\, and the feasibi lity and potential are explored through an experiment. The noise reduction technique leverages destructive interference of the coherent acoustic sou rce field between a system of propellers by controlling the relative phase between the blades in a multi-rotor configuration. In the first stage\, a low-noise and aerodynamically efficient single-rotor configuration based on APC 14x5.5 propeller was designed. The design was based on modelling th e static aerodynamic loads on the blade with Blade Element Momentum Theory . The assumption is that aerodynamic efficiency will result in the reducti on of the sound propagation of the blade. In the second stage\, single and multi-rotor configuration experiments were studied experimentally.\n\nThe single and the multi-rotor configurations were part of a measurement camp aign conducted in the newly established anechoic chamber at the Faculty of Aerospace Engineering at the Technion - Israel Institute of Technology. A n array of 15 microphones were placed 1.5 meters away from the center of t he rotors' rig on a spherical arc. In the multi-rotor configuration\, by c arefully selecting the relative azimuths blade angle (phase)\, the overall sound pressure directivity and level of the tonal component at the blade passage frequency can be attenuated. It was found that with destructive in terference\, a 90 degrees of phase angle between neighbouring rotors\, a r eduction of 4 dB at 3000 RPM and by 7 dB at 3800 RPM was observed\, compar ed to uncontrolled configuration. Measured sound pressure levels were comp ared to the analytical acoustic model\, and similar amplitudes and trends of the sound pressure levels were found between the model and the measurem ents.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-1278@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230911T013000 DTEND;TZID=Asia/Jerusalem:20230911T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-09-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-547@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230911T133000 DTEND;TZID=Asia/Jerusalem:20230911T143000 DTSTAMP:20230824T133214Z URL:https://aerospace.technion.ac.il/events/multiwall-shear-deformable-ort hotropic-plates-moderate-large-deflections-nonlinear-analysis-through-appr oximate-methods-and-tests/ SUMMARY:Multiwall shear deformable orthotropic plates: moderate large defle ctions nonlinear analysis: through approximate methods and tests DESCRIPTION:Lecturer:Gilad Hakim \n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Cl assroom 165\, ground floor\, Library\, Aerospace Eng\n Zoom: https://techn ion.zoom.us/j/97346140543\n Abstract: This lecture presents the behavior o f rectangular plates for an equally distributed load acting perpendicular to the surface. When the resulting deflections are relatively small\, this problem has known analytical solutions. On the other hand\, when the load and deflection are large\, compressive and tensile in-plane forces are cr eated in the plate that cause the plate to stiffen\, the behavior is non-l inear\, and the solutions are only approximated.\nTwo types of plates were studied: a thin plate made of an isotropic material and a relatively thic k hollow plate with an internal structure of different shapes. The hollow plate is homogenized into a thick orthotropic plate subject to shear defor mations in its cross-section.\nThe results of the research were summarized in 5 articles\, three of which have already been published and two are un der peer review.\nThe behavior of the plates is described by the von Kárm án equations set\, which does not have a closed analytical solution for a rectangular plate. Therefore\, a number of Finite Element Analyses were p erformed that allow to present the defections and stresses that are develo ped in the plate. The resulting membrane stress image shows the dangerous points on the plate and suggests ways to reduce the risk.\nCalculating the partial derivatives of the deflection and the stress numerically makes it possible to place them within the equations and to demonstrate the correc tness of the equations in certain areas of the plate. In addition to this\ , the use of statistical methods results in empirical expressions that rep resent the deflections and stresses in plates of different sizes and mater ials.\nAnalytical methods for calculating the equivalent elastic constants of hollow plates with a simple internal structure\, and methods for measu ring the constants in plates with a complex structure are presented. Also\ , surprising results will be presented in the analysis of thin rectangular plates with a large aspect ratio.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-1279@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230913T013000 DTEND;TZID=Asia/Jerusalem:20230913T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-09-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1280@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230918T013000 DTEND;TZID=Asia/Jerusalem:20230918T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-09-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1281@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230920T013000 DTEND;TZID=Asia/Jerusalem:20230920T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-09-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1282@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230925T013000 DTEND;TZID=Asia/Jerusalem:20230925T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-09-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1283@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20230927T013000 DTEND;TZID=Asia/Jerusalem:20230927T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-09-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1284@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231002T013000 DTEND;TZID=Asia/Jerusalem:20231002T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1285@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231004T013000 DTEND;TZID=Asia/Jerusalem:20231004T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1286@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231009T013000 DTEND;TZID=Asia/Jerusalem:20231009T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-548@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231009T133000 DTEND;TZID=Asia/Jerusalem:20231009T143000 DTSTAMP:20230913T130026Z URL:https://aerospace.technion.ac.il/events/a-new-computational-landing-gu idance-algorithm-for-reusable-launch-vehicles/ SUMMARY:A New Computational Landing Guidance Algorithm for Reusable Launch Vehicles DESCRIPTION:Lecturer:Prof. Chang-Hun Lee\n Faculty:Korea Advanced Institute of Science and Technology (KAIST)\n Institute:Korea Advanced Institute of Science and Technology (KAIST)\, Republic of Korea\n Location:Classroom 1 65\, ground floor\, Library\, Aerospace Eng\n Zoom: https://technion.zoom. us/j/983 6793 1661\n Abstract: This talk introduces the optimal landing gu idance\, based on the computational guidance and control (CG&\;C) philo sophy\, for Reusable Launch Vehicles (RLVs) that utilize retro-propulsion for the landing. Recently developed RLVs proved the cost-effectiveness and even the improved flexibility in the operation by reusing the first stage booster. However\, the guidance and control algorithms required for the r eusable launch vehicle not only have to pursue the minimization of fuel us age but also satisfy the various path constraints of the launch vehicle wh ile guaranteeing a precise and soft landing. To mitigate this difficulty\, this study proposes optimal trajectory tracking guidance by model predict ive control (MPC) framework to accomplish soft landing while satisfying th e various constraints. The proposed algorithms comprise two phases: Attain ing the fuel-optimal landing trajectory and tracking the optimal trajector y via MPC. In formulating the optimization problem for the MPC\, the attit ude control and throttling characteristics of the launch vehicle are augme nted while retaining the required computational load. Then\, sequential co nvex programming (SCP) is employed to solve the formulated non-convex opti mization problem efficiently. Lastly\, the proposed algorithm is verified by numerical simulation with a 6DOF model and control algorithm designed f or the assumed launch vehicle and its landing scenario.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng END:VEVENT BEGIN:VEVENT UID:0-1287@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231011T013000 DTEND;TZID=Asia/Jerusalem:20231011T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1288@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231016T013000 DTEND;TZID=Asia/Jerusalem:20231016T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1289@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231018T013000 DTEND;TZID=Asia/Jerusalem:20231018T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1290@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231023T013000 DTEND;TZID=Asia/Jerusalem:20231023T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1291@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231025T013000 DTEND;TZID=Asia/Jerusalem:20231025T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1292@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231030T013000 DTEND;TZID=Asia/Jerusalem:20231030T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-10-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-569@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231030T153000 DTEND;TZID=Asia/Jerusalem:20231030T163000 DTSTAMP:20231023T143904Z URL:https://aerospace.technion.ac.il/events/topology-optimization-of-thin- walled-structures/ SUMMARY:Topology optimization of thin-walled structures DESCRIPTION:Lecturer:Ameer Marzok\n Faculty: Postdoctoral Researcher | The Department of Civil Engineering and Engineering Mechanics\n Institute: Col umbia University\n Location:\n Zoom: https://technion.zoom.us/j/983679316 61 \n Abstract: Thin-walled structures find applications in various discip lines\, including aerospace\, civil\, and mechanical engineering\, thanks to their high stiffness-to-mass ratio. Recent advancements in manufacturin g processes\, which enable the production of structural elements with comp lex geometries\, have made topology optimization an integral part of the d esign process.\n\nThe intricate cross-sections of thin-walled beams result in complex deformation modes that are not adequately captured by traditio nal beam theories\, especially when torsional behavior is expected. In add ition\, these elements are prone to buckling due to their slenderness.\n\n In this presentation\, we will discuss a recently developed efficient topo logy optimization method for designing these elements. The method relies o n a density-based approach that is solved iteratively using an efficient g radient-based optimization framework\, allowing for a large number of desi gn variables. The optimization problem is formulated considering linearize d buckling\, stiffness\, and stress constraints.\n\nThe solution procedure of the optimization problem involves a large number of analyses of differ ent designs\, making traditional 3D FEM formulations impractical for such a problem. Therefore\, we have developed a novel method for the analysis o f these elements consisting of a 3D finite element mesh enhanced with glob al enrichment functions\, utilizing the XFEM method. These global enrichme nt functions incorporate physical knowledge about the expected behavior of the beam\, allowing for a substantial reduction in the computational burd en.\n\nThe results demonstrate that the proposed approach allows designing these elements while considering various performance constraints.\n Detai ls: \n CATEGORIES:Seminars END:VEVENT BEGIN:VEVENT UID:0-1293@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231101T013000 DTEND;TZID=Asia/Jerusalem:20231101T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1294@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231106T013000 DTEND;TZID=Asia/Jerusalem:20231106T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1295@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231108T013000 DTEND;TZID=Asia/Jerusalem:20231108T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1296@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231113T013000 DTEND;TZID=Asia/Jerusalem:20231113T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1297@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231115T013000 DTEND;TZID=Asia/Jerusalem:20231115T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1298@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231120T013000 DTEND;TZID=Asia/Jerusalem:20231120T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1299@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231122T013000 DTEND;TZID=Asia/Jerusalem:20231122T023000 DTSTAMP:20251118T063914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1300@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231127T013000 DTEND;TZID=Asia/Jerusalem:20231127T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1301@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231129T013000 DTEND;TZID=Asia/Jerusalem:20231129T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-11-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-787@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231129T133000 DTEND;TZID=Asia/Jerusalem:20231129T143000 DTSTAMP:20231115T122717Z URL:https://aerospace.technion.ac.il/events/aero-thermal-elasticity-of-pla tes-in-hypersonic-flow/ SUMMARY:Aero-thermal-elasticity of plates in hypersonic flow DESCRIPTION:Lecturer:Maxim Freydin\, PhD\n Faculty:Department of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Loca tion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https ://technion.zoom.us/j/93899557822\n Abstract: Fluid-structure interaction in high-speed flow has seen an increased interest among researchers in res ponse to the worldwide race to sustainable hypersonic flight. The interact ion between inertial\, elastic\, aerodynamic\, and thermal loads in high M ach flows is an extension of classical aeroelasticity. To investigate the fundamental physics that govern the aero-thermal-elastic interaction\, ela stic plates are utilized in wind tunnel experiments for their relative sim plicity of installation\, manufacture\, and analysis. Recent experiments i nvestigate the response of elastic plates using advanced measurement techn iques for pressure\, temperature\, and deformation. This enables a detaile d and direct correlation between theoretical and computational results cov ering a wide range of phenomena including shock-wave/boundary-layer and st ructure interaction\, flutter onset\, limit-cycle oscillation\, and imping ing shocks. In this talk\, a theoretical-computational model of plates in hypersonic flow is presented\, and its use for the analysis of linear and nonlinear static and dynamic problems is demonstrated. Recent extensions o f the model are presented with unsteady aerodynamic heating and piezoelect ric patches that double as strain sensors and structural elements. Importa nt parts of the structure and fluid models are emphasized through the lens of fluid-structure interaction including non-ideally clamped in-plane bou ndary conditions and turbulent pressure fluctuations.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1302@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231204T013000 DTEND;TZID=Asia/Jerusalem:20231204T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-12-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1303@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231206T013000 DTEND;TZID=Asia/Jerusalem:20231206T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-12-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1304@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231211T013000 DTEND;TZID=Asia/Jerusalem:20231211T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-12-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1305@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231213T013000 DTEND;TZID=Asia/Jerusalem:20231213T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-12-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1306@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231218T013000 DTEND;TZID=Asia/Jerusalem:20231218T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-12-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1307@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231220T013000 DTEND;TZID=Asia/Jerusalem:20231220T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-12-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1308@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231225T013000 DTEND;TZID=Asia/Jerusalem:20231225T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-12-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1309@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20231227T013000 DTEND;TZID=Asia/Jerusalem:20231227T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2023-12-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1310@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240101T013000 DTEND;TZID=Asia/Jerusalem:20240101T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1311@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240103T013000 DTEND;TZID=Asia/Jerusalem:20240103T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1312@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240108T013000 DTEND;TZID=Asia/Jerusalem:20240108T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1313@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240110T013000 DTEND;TZID=Asia/Jerusalem:20240110T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1314@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240115T013000 DTEND;TZID=Asia/Jerusalem:20240115T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1315@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240117T013000 DTEND;TZID=Asia/Jerusalem:20240117T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1316@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240122T013000 DTEND;TZID=Asia/Jerusalem:20240122T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1317@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240124T013000 DTEND;TZID=Asia/Jerusalem:20240124T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1318@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240129T013000 DTEND;TZID=Asia/Jerusalem:20240129T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1319@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240131T013000 DTEND;TZID=Asia/Jerusalem:20240131T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-01-31/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1320@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240205T013000 DTEND;TZID=Asia/Jerusalem:20240205T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-02-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1321@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240207T013000 DTEND;TZID=Asia/Jerusalem:20240207T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-02-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1322@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240212T013000 DTEND;TZID=Asia/Jerusalem:20240212T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-02-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1323@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240214T013000 DTEND;TZID=Asia/Jerusalem:20240214T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-02-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1324@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240219T013000 DTEND;TZID=Asia/Jerusalem:20240219T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-02-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1325@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240221T013000 DTEND;TZID=Asia/Jerusalem:20240221T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-02-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1326@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240226T013000 DTEND;TZID=Asia/Jerusalem:20240226T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-02-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1327@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240228T013000 DTEND;TZID=Asia/Jerusalem:20240228T023000 DTSTAMP:20251118T063913Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-02-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-789@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240228T130000 DTEND;TZID=Asia/Jerusalem:20240228T143000 DTSTAMP:20240226T102328Z URL:https://aerospace.technion.ac.il/events/dr-anna-clarke-skydiving-and-a e/ SUMMARY:Dr. Anna Clarke - Skydiving and AE DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Auditorium 235 \, The Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: \n Details: \n \n\nIt is very interesting to analyze skydiving from a perspe ctive of control engineering. Skydiving includes two stages:\n\n(1). Perfo rming solo and cooperative aerial maneuvers in free-fall by changing the b ody posture and thus deflecting the surrounding airflow\;\n\n(2). Piloting and landing a high-performance RAM Air parachute. In this talk we will ex plain the challenging aspects of both stages\, describe the on-going resea rch and most interesting results\, and outline the future research opportu nities. ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2022/10/anna-clarke-2.jpg CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-790@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240228T130000 DTEND;TZID=Asia/Jerusalem:20240228T143000 DTSTAMP:20240226T102754Z URL:https://aerospace.technion.ac.il/he/events/%d7%93%d7%a8-%d7%90%d7%a0%d 7%94-%d7%a7%d7%9c%d7%90%d7%a8%d7%a7-%d7%a6%d7%a0%d7%99%d7%97%d7%94-%d7%97% d7%95%d7%a4%d7%a9%d7%99%d7%aa-%d7%95%d7%94%d7%a0%d7%93%d7%a1%d7%aa-%d7%90% d7%95%d7%95%d7%99/ SUMMARY:ד"ר אנה קלארק - צניחה חופשית והנדסת או וירונאוטיקה DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:אודיטוריו ם 235 - הפקולטה להנדסת אוירונוטיקה וחלל\n Zo om: \n Abstract: \n Details: \n \n\nבצהרי יום רביעי 28.3 נא רח את ד"ר אנה קלארק\, עמיתת מחקר בפקולטה\, שתספר לנו על החיבור בין שתי אהבות שלה: מח קרי אווירו וצניחה חופשית.\n\nכצנחנית 🪂 עם למעלה מ 2000 צניחות חופשיות ושיא עולם (!)\, ד "ר קלארק חוקרת צניחות חופשיות מנקודת המב ט של הנדסת בקרה.\n\nבהרצאתה תחשוף אנה את הה יבטים המאתגרים של שלבי הצניחה החופשית\, ת תאר את המחקר המתמשך והתוצאות המעניינות ב יותר\, ותסקור את הזדמנויות המחקר העתידיו ת שניתן להשתלב בהן. ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2022/10/anna-clarke-2.jpg CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-788@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240228T133000 DTEND;TZID=Asia/Jerusalem:20240228T143000 DTSTAMP:20240226T084237Z URL:https://aerospace.technion.ac.il/events/skydiving-from-control-enginee ring-perspective/ SUMMARY:Skydiving From Control Engineering Perspective DESCRIPTION:Lecturer:Dr. Anna Clarke \n Faculty:Department of Aerospace Eng ineering\n Institute:Technion – Israel Institute of Technology\n Locatio n:Auditorium 235\, second floor\, Aerospace Eng. Building\n Zoom: \n Abstr act: It is very interesting to analyze skydiving from a perspective of con trol engineering. Skydiving includes two stages:\n(1). Performing solo and cooperative aerial maneuvers in free-fall by changing the body posture an d thus deflecting the surrounding airflow\;\n(2). Piloting and landing a h igh-performance RAM Air parachute. In this talk we will explain the challe nging aspects of both stages\, describe the on-going research and most int eresting results\, and outline the future research opportunities.\n Detail s: \n CATEGORIES:Seminars LOCATION:Auditorium 235\, second floor\, Aerospace Eng. Building END:VEVENT BEGIN:VEVENT UID:0-1328@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240304T013000 DTEND;TZID=Asia/Jerusalem:20240304T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-03-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1329@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240306T013000 DTEND;TZID=Asia/Jerusalem:20240306T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-03-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-791@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240306T133000 DTEND;TZID=Asia/Jerusalem:20240306T143000 DTSTAMP:20240229T141134Z URL:https://aerospace.technion.ac.il/events/fluidic-shaping-of-optical-com ponents-from-eyeglasses-to-giant-space-telescopes/ SUMMARY:Fluidic shaping of optical components - from eyeglasses to giant sp ace telescopes DESCRIPTION:Lecturer:Prof. Moran Bercovici \n Faculty:Department of Mechani cal Engineering\n Institute:Technion – Israel Institute of Technology\n Location:Auditorium 235\, Second floor\, Aerospace Eng.\n Zoom: \n Abstrac t: The lecture will focus on a novel method we developed\, in which surfac e tension is leveraged to shape a volume of liquid into a useful optical c omponent under microgravity conditions.  In the first part of the talk I will show how we simulate microgravity conditions in the lab\, and the pot ential applications of the technology on Earth.  In the second part I wil l discuss our collaboration with NASA to create liquid-based giant space t elescopes that overcome launch constraints. I will present our microgravit y experiments in parabolic flights\, and the experiments we conducted on b oard the International Space Station.\n\n Details: \n CATEGORIES:Seminars LOCATION:Auditorium 235\, Second floor\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1330@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240311T013000 DTEND;TZID=Asia/Jerusalem:20240311T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-03-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1331@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240313T013000 DTEND;TZID=Asia/Jerusalem:20240313T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-03-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1332@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240318T013000 DTEND;TZID=Asia/Jerusalem:20240318T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-03-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1333@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240320T013000 DTEND;TZID=Asia/Jerusalem:20240320T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-03-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1334@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240325T013000 DTEND;TZID=Asia/Jerusalem:20240325T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-03-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1335@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240327T013000 DTEND;TZID=Asia/Jerusalem:20240327T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-03-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-800@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240328T110000 DTEND;TZID=Asia/Jerusalem:20240328T120000 DTSTAMP:20240325T073643Z URL:https://aerospace.technion.ac.il/events/simplification-for-efficient-d ecision-making-under-uncertainty-with-general-distributions/ SUMMARY:Simplification for Efficient Decision Making Under Uncertainty with General Distributions DESCRIPTION:Lecturer:Andrey Zhitnikov \n Faculty:TASP\n Institute:Technion – Israel Institute of Technology\n Location:Zoom\n Zoom: https://eur01.s afelinks.protection.outlook.com/?url=https%3A%2F%2Ftechnion.zoom.us%2Fj%2F 92401602138%3Fpwd%3DcUt5SVlkWHJoQW5IMFJ5ejJIRlFmZz09&\;data=05%7C02%7Ca eug-assistant%40technion.ac.il%7C782343b3aa0549112d6608dc40ddfaa8%7Cf1502c 4cee2e411c9715c855f6753b84%7C1%7C0%7C638456571053068967%7CUnknown%7CTWFpbG Zsb3d8eyJWIjoiMC4wLjAwMDAiLCJQIjoiV2luMzIiLCJBTiI6Ik1haWwiLCJXVCI6Mn0%3D%7 C0%7C%7C%7C&\;sdata=5GyPEem4R49tAIVVMb2rJ2%2FEC5YR8LjiZgndCpBLcUU%3D&am p\;reserved=0\n Abstract: \n\n\n\nPlanning under uncertainty in partially observable domains\, also known as Belief Space Planning (BSP)\, is an ess ential scientific inquiry to create Artificial Intelligence and a recurren t aspect in many real-life scenarios. The prevailing way to formulate such a decision making is the Partially Observable Markov Decision Process (PO MDP). The POMDP is notoriously hard to solve due to the multitude of possi ble future robot actions and observations along the planning horizon.\nIn this research\, we address the problem of efficient online BSP in continuo us domains. Towards this end\, we first introduce the adaptive multilevel simplification paradigm\, which aims to accelerate decision-making while p roviding performance guarantees. We then suggest a novel Probabilistic POM DP formulation that takes into account the variability of the POMDP elemen ts stemming from nonparametric representations. Based on this extension we formulate stochastic bounds over the cumulative robot reward and perform risk-aware BSP efficiently considering state-dependent rewards and informa tion-theoretic rewards\, such as differential entropy. In this work\, we s uggest an adaptive scheme to evaluate the theoretical differential entropy over a general belief surface. Finally\, we focus on Constrained POMDP. H ere\, we propose a novel Probabilistically Constrained belief-dependent PO MDP. Our constraint operator is belief-dependent for the first time to the best of our knowledge. It can be information related in the context of ex ploration or motivated by safety aspects. In both settings\, we accelerate online planning while providing guarantees on the impact of the accelerat ion.\n\n\n\n\n Details: \n CATEGORIES:Seminars LOCATION:Zoom END:VEVENT BEGIN:VEVENT UID:0-1336@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240401T013000 DTEND;TZID=Asia/Jerusalem:20240401T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1337@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240403T013000 DTEND;TZID=Asia/Jerusalem:20240403T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-792@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240403T123000 DTEND;TZID=Asia/Jerusalem:20240403T143000 DTSTAMP:20240229T122431Z URL:https://aerospace.technion.ac.il/events/focus-on-iai/ SUMMARY:Focus on IAI DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:\n Zoom: \n Ab stract: \n Details: \n The Israel Aerospace Industries will host a "Spotli ght Day" at the faculty with a special focus on career opportunities for a erospace engineering students and graduates. CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-793@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240403T123000 DTEND;TZID=Asia/Jerusalem:20240403T143000 DTSTAMP:20240229T123036Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%96%d 7%a8%d7%a7%d7%95%d7%a8-%d7%a2%d7%9d-%d7%94%d7%aa%d7%a2%d7%a9%d7%99%d7%94-% d7%94%d7%90%d7%95%d7%95%d7%99%d7%a8%d7%99%d7%aa/ SUMMARY:יום זרקור עם התעשיה האווירית DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n צהרי יום ד' יוקדשו לחשיפה לתעש יה האווירית\, לפעילות החטיבות השונות ולא פשרויות השתלבות ופיתוח קריירה לסטודנטים בפקולטה ולמהנדסי אוירונוטיקה וחלל.\n\n CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-801@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240404T110000 DTEND;TZID=Asia/Jerusalem:20240404T120000 DTSTAMP:20240325T074239Z URL:https://aerospace.technion.ac.il/events/simplified-pomdp-algorithms-wi th-performance-guarantees/ SUMMARY:Simplified POMDP Algorithms with Performance Guarantees DESCRIPTION:Lecturer:Moran Barenboim\n Faculty:TASP\n Institute:Technion – Israel Institute of Technology\n Location:Zoom\n Zoom: https://technio n.zoom.us/j/91734030277?pwd=TUNEc3BkNzhLNXdxQVBoVGhOc0hwZz09\n Abstract: \ n\n\n\nAutonomous agents operating in real-world scenarios frequently enco unter uncertainty and make decisions based on incomplete information. This challenge can be structured mathematically through the lens of partially observable Markov decision processes (POMDPs). While POMDPs offer a robust framework for planning under uncertainty\, finding an optimal plan for a POMDP can be computationally intensive and is feasible only for simpler ta sks. In response\, the last two decades have witnessed the rise of approxi mate algorithms\, like tree search and sample-based approaches\, as leadin g solutions for tackling more complex POMDP problems. Despite their effect iveness\, these algorithms typically offer only probabilistic guarantees o r\, in some cases\, no formal guarantees at all.\nIn our research\, we hav e focused on addressing these limitations by developing a range of simplif ied algorithms with formal\, deterministic guarantees. These simplified al gorithms operate on a selected subset of the state and observation spaces\ , commonly considered in state-of-the-art algorithms\, while providing mat hematical guarantees and computational efficiencies compared to the non-si mplified algorithm. Initially\, we focused on a belief-dependent reward fr amework\, simplifying the reward calculation by narrowing down the observa tion space. Then\, we have applied a simplification to the state space in the context of hybrid-belief and data-association aware POMDPs\, which oth erwise may grow exponentially. Ultimately\, we extended our approach to a broad POMDP framework\, simplifying both state and observation spaces\, an d providing deterministic guarantees with respect to the optimal solution. \n\n\n\n\n Details: \n CATEGORIES:Seminars LOCATION:Zoom END:VEVENT BEGIN:VEVENT UID:0-1338@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240408T013000 DTEND;TZID=Asia/Jerusalem:20240408T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1339@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240410T013000 DTEND;TZID=Asia/Jerusalem:20240410T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1340@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240415T013000 DTEND;TZID=Asia/Jerusalem:20240415T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-802@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240416T110000 DTEND;TZID=Asia/Jerusalem:20240416T120000 DTSTAMP:20240331T070615Z URL:https://aerospace.technion.ac.il/events/structure-aware-probabilistic- inference-and-belief-space-planning-with-performance-guarantees/ SUMMARY:Structure Aware Probabilistic Inference and Belief Space Planning w ith Performance Guarantees DESCRIPTION:Lecturer:Moshe Shienman\n Faculty:Technion Autonomous Systems P rogram\n Institute:Technion – Israel Institute of Technology\n Location: Zoom\n Zoom: https://technion.zoom.us/j/95719271567?pwd=WUNGZjVxS1A2bG5TZF RvRDBBN3NSUT09\n Abstract: \n\n\n\nIntelligent autonomous agents and robot s are increasingly utilized across various domains\, impacting our daily l ives in significant ways. From robotic surgery to automated warehousing\, these agents are often expected to operate reliably and efficiently despit e facing limited environmental knowledge and uncertainty. Uncertainty aris es from various factors\, including noisy or restricted observations due t o physical constraints\, imprecise action execution\, and unpredictable ev ents in dynamic environments. In such scenarios\, a truly autonomous agent should be able to perform both inference\, which involves maintaining a b elief over the high-dimensional state based on available information\, and decision making under uncertainty\, also known as Belief Space Planning ( BSP). In BSP\, the agent autonomously determines its optimal next actions while considering the future evolution of beliefs. However\, solving bot t hese problems is computationally expensive and practically infeasible in r eal-world autonomous systems\, where the agent is required to operate in r eal time\, using inexpensive hardware and limited resources.\nIn our resea rch\, we utilize both topological structures\, induced from graph represen tations of posterior beliefs\, and specific structures of posterior distri butions\, to efficiently perform inference and BSP in high dimensional sta te spaces. Specifically\, for BSP\, we introduce a novel concept that leve rages topological signatures to approximate the solution. We establish ana lytical bounds for this approximation to ensure performance and empiricall y quantify its computational efficiency. In perceptually aliased environme nts\, where data association is not solved and posterior distributions are multi modal\, we leverage the structure of posterior distributions to bou nd the information loss when pruning hypotheses. This enables us to effici ently solve nonmyopic BSP problems without compromising on the quality of the solution. Finally\, we introduce an innovative method for incremental nonparametric probabilistic inference. Our approach leverages slices from high-dimensional surfaces to efficiently approximate posterior distributio ns of any shape.\n\n\n\n Details: \n CATEGORIES:Seminars LOCATION:Zoom END:VEVENT BEGIN:VEVENT UID:0-1341@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240417T013000 DTEND;TZID=Asia/Jerusalem:20240417T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1342@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240422T013000 DTEND;TZID=Asia/Jerusalem:20240422T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1343@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240424T013000 DTEND;TZID=Asia/Jerusalem:20240424T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1344@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240429T013000 DTEND;TZID=Asia/Jerusalem:20240429T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-04-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1345@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240501T013000 DTEND;TZID=Asia/Jerusalem:20240501T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1346@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240506T013000 DTEND;TZID=Asia/Jerusalem:20240506T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1347@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240508T013000 DTEND;TZID=Asia/Jerusalem:20240508T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-796@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240509T093000 DTEND;TZID=Asia/Jerusalem:20240509T170000 DTSTAMP:20240229T125212Z URL:https://aerospace.technion.ac.il/events/iacas-2024/ SUMMARY:IACAS 2024 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n The 63rd Israel Annual Conference on Aerospace Sciences \, spanning several generations\, is an important annual event on the cale ndar of the aerospace community in Israel and arouses great interest abroa d. In this yearly event are engineers\, scientists\, and experts in the fi eld of aeronautics and astronautics\, representing well-known local aerosp ace agencies and industries and participants from major research centers w orldwide.\n\nCheck out the IACAS website at: https://iacas.technion.ac.il/ \n\n CATEGORIES:Events END:VEVENT BEGIN:VEVENT UID:0-797@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240509T093000 DTEND;TZID=Asia/Jerusalem:20240509T170000 DTSTAMP:20240229T125800Z URL:https://aerospace.technion.ac.il/he/events/iacas-2024/ SUMMARY:IACAS 2024 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n הכנס הישראלי השנתי ה-63  למדעי התעופה והחלל הוא האירוע השנתי החשוב בלוח השנה של קהילת התעופה והחלל בישראל ומעור ר עניין רב גם בחו"ל. באירוע לוקחים חלק מהנ דסים\, מדענים ומומחים בתחום האווירונאוטי קה והאסטרונאוטיקה\, המייצגים סוכנויות ות עשיות תעופה וחלל מקומיות\, כמו גם משתתפים ממרכזי מחקר גדולים ברחבי העולם.\n\nכל הפר טים באתר הכנס: https://iacas.technion.ac.il/\n\n CATEGORIES:אירועים END:VEVENT BEGIN:VEVENT UID:0-1348@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240513T013000 DTEND;TZID=Asia/Jerusalem:20240513T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1349@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240515T013000 DTEND;TZID=Asia/Jerusalem:20240515T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1350@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240520T013000 DTEND;TZID=Asia/Jerusalem:20240520T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1351@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240522T013000 DTEND;TZID=Asia/Jerusalem:20240522T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1352@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240527T013000 DTEND;TZID=Asia/Jerusalem:20240527T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1353@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240529T013000 DTEND;TZID=Asia/Jerusalem:20240529T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-05-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-794@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240529T123000 DTEND;TZID=Asia/Jerusalem:20240529T143000 DTSTAMP:20240229T124046Z URL:https://aerospace.technion.ac.il/events/research-day-2024/ SUMMARY:Research Day 2024 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Faculty of Aerospa ce Engineering\n Zoom: \n Abstract: \n Details: \n Our Graduate Studies Re search Day is an annual event that attracts not only Aerospace Engineering students and faculty members but also students from around the campus and aerospace professionals from the industry. The graduate students will pre sent their research posters to the audience.\n\nAs part of the tradition\, a judging committee chose the best posters of M.Sc. and Ph.D. students. I n addition\, the crowd picked its favorite.\n\n CATEGORIES:Events LOCATION:Faculty of Aerospace Engineering END:VEVENT BEGIN:VEVENT UID:0-795@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240529T123000 DTEND;TZID=Asia/Jerusalem:20240529T143000 DTSTAMP:20240229T124318Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%94%d 7%9e%d7%97%d7%a7%d7%a8-2024/ SUMMARY:יום המחקר 2024 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:דשא הפקול טה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: \n Details: \n יום המחקר הפקולטי לתארים מתקדמים הוא אירוע שנתי שמושך לא רק סטודנטים וחבר י סגל להנדסת אוירונוטיקה וחלל\, אלא גם סט ודנטים מרחבי הקמפוס\, כמו גם אנשי מקצוע ב תחום התעופה והחלל מהתעשייה. הסטודנטים לת ארים שני ודוקטורט מציגים את פרי המחקרים שלהם לקהל באירוע הפנינג שנתי גדול.\n\nכחלק מהמסורת\, ועדת שיפוט בוחרת את המחקרים הנ בחרים. בנוסף\, הקהל מצביע ובוחר את המחקר ח ביב הקהל.\n\n CATEGORIES:אירועים LOCATION:דשא הפקולטה להנדסת אוירונוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1354@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240603T013000 DTEND;TZID=Asia/Jerusalem:20240603T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-06-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1355@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240605T013000 DTEND;TZID=Asia/Jerusalem:20240605T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-06-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1356@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240610T013000 DTEND;TZID=Asia/Jerusalem:20240610T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-06-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1357@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240612T013000 DTEND;TZID=Asia/Jerusalem:20240612T023000 DTSTAMP:20251118T063912Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-06-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1358@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240617T013000 DTEND;TZID=Asia/Jerusalem:20240617T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-06-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1359@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240619T013000 DTEND;TZID=Asia/Jerusalem:20240619T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-06-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-805@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240619T133000 DTEND;TZID=Asia/Jerusalem:20240619T143000 DTSTAMP:20240609T061511Z URL:https://aerospace.technion.ac.il/events/the-2024-prize-seminar-in-memo ry-of-prof-shmuel-and-mrs-noemi-merhav/ SUMMARY:The 2024 PhD Seminar in Memory of Prof. Shmuel and Mrs. Noemi Merha v – Theoretical Thermodynamic and Hydrodynamic Study of Liquids Under Ne gative Pressures. DESCRIPTION:Lecturer:Orr Avni\n Faculty:Department of Aerospace Engineering \n Institute:Technion – Israel Institute of Technology\n Location:Classr oom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://technion .zoom.us/j/93899557822\n Abstract: When a liquid is subjected to a press ure below absolute zero\, the phase change becomes favorable\; however\, t he attractive interactions between the liquid molecules may hinder the pha se change process. From a mechanical standpoint\, the liquid stretches as the internal tension stresses\, or negative hydrostatic pressures\, devel op in the liquid bulk. Liquids subjected to negative pressure are abundant and could be utilized in several industrial and medical applications. S ome promising industrial innovations harness this phenomenon\, while other s seek to control and direct the nucleation occurring as the liquid relaxe s back to a stable state.\n\nHuygens made the first experimental observati ons of liquids under negative absolute pressures as early as 1662. Since t hen\, numerous experimental apparatuses have been developed to generate negative pressure in liquids. However\, a significant discrepancy exists between the maximum negative pressure a liquid can sustain before nucleati on onset\, as reported in different experiments. This gap\, which may exc eed 100 MPa\, is yet unexplained\, raising fundamental questions about the nature of liquids under extreme thermodynamic states and limiting the rel iable application of this phenomenon.\n\nAiming to bridge the gap in curre nt knowledge\, we first focus on the surface tension-controlled\, near-equ ilibrium growth of vapor bubbles. We present a new analysis for the early stages of vapor bubble growth in superheated liquids capable of capturing the early stages of bubble growth. We extend the analytic investigation by an extensive numerical study\, enabling a detailed analysis of vapor bubb le dynamics under highly oscillating negative pressures. The presented the oretical model may reveal possible future research pathways for better und erstanding the elusive and fascinating nature of liquids under negative pr essure.\n\nWork towards PhD degree under the supervision of Asst. Prof. Yu val Dagan and Prof. Eran Sher\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1360@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240624T013000 DTEND;TZID=Asia/Jerusalem:20240624T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-06-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1361@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240626T013000 DTEND;TZID=Asia/Jerusalem:20240626T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-06-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-803@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240626T130000 DTEND;TZID=Asia/Jerusalem:20240626T141500 DTSTAMP:20240521T132050Z URL:https://aerospace.technion.ac.il/events/faculty-concert-2/ SUMMARY:Faculty Concert DESCRIPTION:Lecturer:\n Faculty:Faculty of Aerospace Engineering\n Institut e:\n Location:Auditorium 235\n Zoom: \n Abstract: \n Details: \n AE Rocks! \nSupertalented faculty members and students will play and sing at the 5th Annual Faculty Concert.\n\n \;\n\nPhotos from past faculty concerts\n \n CATEGORIES:Events LOCATION:Auditorium 235 END:VEVENT BEGIN:VEVENT UID:0-804@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240626T130000 DTEND;TZID=Asia/Jerusalem:20240626T143000 DTSTAMP:20240626T042645Z URL:https://aerospace.technion.ac.il/he/events/%d7%a7%d7%95%d7%a0%d7%a6%d7 %a8%d7%98-%d7%a4%d7%a7%d7%95%d7%9c%d7%98%d7%99-2/ SUMMARY:קונצרט פקולטי DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:\n Location:אודיטוריום 235 \n Zoom : \n Abstract: \n Details: \n הקונצרט הפקולטי חוזר!\nס טודנטים וחברי סגל מוכשרים ינגנו וישירו ב קונצרט השנתי החמישי של הפקולטה. \n\n\n\nתמו נות מקונצרטים קודמים:\n\n CATEGORIES:אירועים LOCATION:אודיטוריום 235 END:VEVENT BEGIN:VEVENT UID:0-1362@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240701T013000 DTEND;TZID=Asia/Jerusalem:20240701T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1363@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240703T013000 DTEND;TZID=Asia/Jerusalem:20240703T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-798@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240704T173000 DTEND;TZID=Asia/Jerusalem:20240704T183000 DTSTAMP:20240704T101514Z URL:https://aerospace.technion.ac.il/events/excellence-awards-ceremony/ SUMMARY:Excellence Awards Ceremony DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Dan Kahn Building\ , Mechanical Eng. - Auditorium\n Zoom: \n Abstract: \n Details: \n Annual Excellence Awards Ceremony for students and faculty\, winter and spring te rms 2022-2023 CATEGORIES:Events LOCATION:Dan Kahn Building\, Mechanical Eng. - Auditorium END:VEVENT BEGIN:VEVENT UID:0-799@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240704T173000 DTEND;TZID=Asia/Jerusalem:20240704T183000 DTSTAMP:20240704T105539Z URL:https://aerospace.technion.ac.il/he/events/%d7%98%d7%a7%d7%a1-%d7%a4%d 7%a8%d7%a1%d7%99-%d7%94%d7%a6%d7%98%d7%99%d7%99%d7%a0%d7%95%d7%aa/ SUMMARY:טקס פרסי הצטיינות DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:אודיטוריו ם בניין דן קאהן\, הפקולטה להנדסת מכונות\n Z oom: \n Abstract: \n Details: \n טקס ציון הענקת תעודות הצטיינות לסטודנטים והענקת פרסי הצטיינות פקולטיים\, סמסטר חורף ואביב תשפ"ג\, שנה"ל תשפ"ד CATEGORIES:אירועים LOCATION:אודיטוריום בניין דן קאהן\, הפקולטה ל הנדסת מכונות END:VEVENT BEGIN:VEVENT UID:0-1364@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240708T013000 DTEND;TZID=Asia/Jerusalem:20240708T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1365@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240710T013000 DTEND;TZID=Asia/Jerusalem:20240710T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-807@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240710T123000 DTEND;TZID=Asia/Jerusalem:20240710T143000 DTSTAMP:20240703T115335Z URL:https://aerospace.technion.ac.il/events/focus-on-the-industry-elbit/ SUMMARY:Focus on the Industry - ELBIT DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty of Aer ospace Engineering Lobby and Auditorium\n Zoom: \n Abstract: Elbit Systems will present their Aerospace business unit and talk about the Elbit UAV d esign and production line.\n\n\n Details: \n CATEGORIES:Events LOCATION:Faculty of Aerospace Engineering Lobby and Auditorium END:VEVENT BEGIN:VEVENT UID:0-808@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240710T123000 DTEND;TZID=Asia/Jerusalem:20240710T143000 DTSTAMP:20240703T115956Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%96%d 7%a8%d7%a7%d7%95%d7%a8-%d7%97%d7%98%d7%99%d7%91%d7%aa-%d7%9b%d7%9c%d7%99-% d7%98%d7%99%d7%a1-%d7%91%d7%90%d7%9c%d7%91%d7%99%d7%98/ SUMMARY:יום זרקור - חטיבת כלי טיס באלביט DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:הטכניון - מכון טכנולוגי לישראל\n Location:לובי ואודיטוריום הפקולטה\n Z oom: \n Abstract: חטיבת כלי הטיס של אלביט יגיעו ל פקולטה ליום זרקור.\n\nבתוכנית:\n\n הכרות עם מנהלי חטיבת כלי הטיס\n הרצאה בנושא פיתוח י כטב"מים\n פרטים על גיוסים לאלביט\n כיבו ד ונשנושים!\n\n\n Details: \n CATEGORIES:אירועים LOCATION:לובי ואודיטוריום הפקולטה END:VEVENT BEGIN:VEVENT UID:0-1366@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240715T013000 DTEND;TZID=Asia/Jerusalem:20240715T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1367@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240717T013000 DTEND;TZID=Asia/Jerusalem:20240717T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1368@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240722T013000 DTEND;TZID=Asia/Jerusalem:20240722T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1369@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240724T013000 DTEND;TZID=Asia/Jerusalem:20240724T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-809@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240724T123000 DTEND;TZID=Asia/Jerusalem:20240724T143000 DTSTAMP:20240709T091342Z URL:https://aerospace.technion.ac.il/events/the-1st-annual-gvahim-excellen ce-program-event/ SUMMARY:The 1st annual GVAHIM excellence program event DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Classroom 165\ , ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1370@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240729T013000 DTEND;TZID=Asia/Jerusalem:20240729T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1371@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240731T013000 DTEND;TZID=Asia/Jerusalem:20240731T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-07-31/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-816@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240731T123000 DTEND;TZID=Asia/Jerusalem:20240731T143000 DTSTAMP:20240729T101457Z URL:https://aerospace.technion.ac.il/events/focus-on-the-industry-nvidia/ SUMMARY:Focus on the Industry – nVIDIA DESCRIPTION:Lecturer:Introduction to nVIDIA\n Faculty:Department of Aerospa ce Engineering\n Institute:Technion – Israel Institute of Technology\n L ocation:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: \n Details: \n CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-817@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240731T123000 DTEND;TZID=Asia/Jerusalem:20240731T143000 DTSTAMP:20240729T101819Z URL:https://aerospace.technion.ac.il/he/events/%d7%9e%d7%a4%d7%92%d7%a9-%d 7%97%d7%a9%d7%99%d7%a4%d7%94-nvidia/ SUMMARY:מפגש חשיפה - nVIDIA DESCRIPTION:Lecturer:חשיפה לחברת nVIDIA + סדנת HR לכתיב ת קורות חיים\n Faculty:\n Institute:\n Location:אודיטורי ום 235 - הפקולטה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: \n Details: \n CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1372@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240805T013000 DTEND;TZID=Asia/Jerusalem:20240805T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-08-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-815@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240806T130000 DTEND;TZID=Asia/Jerusalem:20240806T140000 DTSTAMP:20240804T095238Z URL:https://aerospace.technion.ac.il/events/novel-class-of-expected-value- bounds-and-applications-in-belief-space-planning/ SUMMARY:Novel Class of Expected Value Bounds and Applications in Belief Spa ce Planning DESCRIPTION:Lecturer:Ohad Levy-Or \n Faculty:TASP\n Institute:Technion – Israel Institute of Technology\n Location:Zoom\n Zoom: https://technion.zo om.us/j/93899557822\n Abstract: Planning under uncertainty in partially ob servable domains\, often formulated as POMDPs\, is an exceedingly difficul t problem. Finding the globally optimal solution is intractable for all bu t the smallest problems as it requires reasoning about realization of the many random variables of the problem. Thus\, tractable bounds with formal guarantees are attractive alternative to finding a globally optimal soluti on. In this paper\, motivated by this line of reasoning\, we formulate and prove novel probability theory bounds. First\, we bound the expectation w ith respect to the partial expectation (seen to be directly proportional t o the conditional expectation) and show that this is a generalization of t he Markov inequality.  Second\, by merging our novel inequalities with Ho effding's inequality\, we compose an additional novel bound\, which allows for bounding expectations with respect to estimators of partial expectati ons. Finally\, we apply these bounds to the context of planning\; we prove bounds on the general value function with respect to the partial observat ion space. We then bound the conditional entropy with respect to the parti al observation space and finally\, with the use of our novel bounds\, leve rage the structure of beliefs in POMDPs to allow for reuse in calculations when eliminating certain realizations of the belief topology.\nThe work i s towards M.Sc. degree under the supervision of Associate Professor Vadim Indelman\, Department of Aerospace Engineering\, Technion – Israel Insti tute of Technology.\n Details: \n CATEGORIES:Seminars LOCATION:Zoom END:VEVENT BEGIN:VEVENT UID:0-1373@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240807T013000 DTEND;TZID=Asia/Jerusalem:20240807T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-08-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-813@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240807T123000 DTEND;TZID=Asia/Jerusalem:20240807T143000 DTSTAMP:20240717T131101Z URL:https://aerospace.technion.ac.il/events/faculty-picnic-3/ SUMMARY:Faculty Picnic DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty yard\n Zoom: \n Abstract: The students' annual event\n\n Details: The students' annual event\n\n CATEGORIES:Events LOCATION:Faculty yard END:VEVENT BEGIN:VEVENT UID:0-814@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240807T123000 DTEND;TZID=Asia/Jerusalem:20240807T143000 DTSTAMP:20240729T101951Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%a4%d7%99%d7%a7%d7 %a0%d7%99%d7%a7-%d7%94%d7%a4%d7%a7%d7%95%d7%9c%d7%98%d7%99/ SUMMARY:הפיקניק הפקולטי DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:הטכניון - מכון טכנולוגי לישראל\n Location:דשא הפקולטה\n Zoom: \n Abstract: האי רוע השנתי של הסטודנטים בפקולטה\n\n Details: \n CATEGORIES:אירועים LOCATION:דשא הפקולטה END:VEVENT BEGIN:VEVENT UID:0-1374@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240812T013000 DTEND;TZID=Asia/Jerusalem:20240812T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-08-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1375@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240814T013000 DTEND;TZID=Asia/Jerusalem:20240814T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-08-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-818@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240814T120000 DTEND;TZID=Asia/Jerusalem:20240814T130000 DTSTAMP:20240808T063343Z URL:https://aerospace.technion.ac.il/events/previous-knowledge-utilization -in-non-parametric-online-belief-space-planning/ SUMMARY:Previous Knowledge Utilization In Non-Parametric Online Belief Spac e Planning DESCRIPTION:Lecturer:Michael Novitsky\n Faculty:TASP\n Institute:Technion – Israel Institute of Technology\n Location:Zoom\n Zoom: https://technio n.zoom.us/j/92048227868\n Abstract: Online planning under uncertainty rema ins a critical challenge in robotics and autonomous systems. While tree se arch techniques are commonly employed to construct partial future trajecto ries within computational constraints\, most existing methods discard info rmation from previous planning sessions. This study presents a novel\, com putationally efficient approach that leverages historical planning data in current decision-making processes in a partially observable setting. We p rovide theoretical foundations for our information reuse strategy and intr oduce an algorithm based on Monte Carlo Tree Search (MCTS) that implements this approach.\nExperimental results demonstrate that our method signific antly reduces computation time while maintaining high performance levels. Our findings suggest that integrating historical planning information can substantially improve the efficiency of online decision-making in uncertai n environments\, paving the way for more responsive and adaptive autonomou s systems.\nThe work is towards M.Sc. degree under the supervision of Asso ciate Professor\, Vadim Indelman\, Head of the Autonomous Navigation and P erception Lab\, Department of Aerospace Engineering\, Technion – Israel Institute of Technology\n Details: \n CATEGORIES:Seminars LOCATION:Zoom END:VEVENT BEGIN:VEVENT UID:0-1376@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240819T013000 DTEND;TZID=Asia/Jerusalem:20240819T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-08-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1377@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240821T013000 DTEND;TZID=Asia/Jerusalem:20240821T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-08-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-810@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240821T130000 DTEND;TZID=Asia/Jerusalem:20240821T143000 DTSTAMP:20240801T061501Z URL:https://aerospace.technion.ac.il/events/nitzan-sadan-the-captain/ SUMMARY:Nitzan Sadan - "The Captain" DESCRIPTION:Lecturer:Nitzan Sadan\n Faculty:Department of Aerospace Enginee ring\n Institute:Technion – Israel Institute of Technology\n Location:Au ditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: \n Details: \n ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2024/07/ניצן.jpg CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-811@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240821T130000 DTEND;TZID=Asia/Jerusalem:20240821T143000 DTSTAMP:20240801T054049Z URL:https://aerospace.technion.ac.il/he/events/%d7%a0%d7%99%d7%a6%d7%9f-%d 7%a1%d7%93%d7%9f-%d7%94%d7%a7%d7%91%d7%a8%d7%a0%d7%99%d7%98/ SUMMARY:ניצן סדן - "הקברניט" DESCRIPTION:Lecturer:ניצן סדן\n Faculty:הפקולטה להנדסת אוירונוטיקה וחלל\n Institute:הטכניון - מכון טכ נולוגי לישראל\n Location:אודיטוריום 235 - הפקו לטה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: \ n Details: \n ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2024/07/ניצן.jpg CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-819@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240822T143000 DTEND;TZID=Asia/Jerusalem:20240822T163000 DTSTAMP:20240820T162546Z URL:https://aerospace.technion.ac.il/events/aerospace-engineering-final-pr ojects-exhibition/ SUMMARY:Aerospace Engineering Final Projects Exhibition DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty of Aer ospace Engineering Lobby \n Zoom: \n Abstract: We are happy to invite you to our undergraduate students' annual event of the Aerospace Engineering Final Projects (7-8).\n\n \;\n\nThursday\, August 22\, 2024  |  2:3 0-4:30 p.m.  |  In the faculty lobby\n\n \;\n\nAt the event\, 13 st udents' final projects will be presented\, accompanied by explanations\, p resentations\, posters\, and models.\n Details: \n CATEGORIES:Events LOCATION:Faculty of Aerospace Engineering Lobby END:VEVENT BEGIN:VEVENT UID:0-820@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240822T143000 DTEND;TZID=Asia/Jerusalem:20240822T163000 DTSTAMP:20240820T163203Z URL:https://aerospace.technion.ac.il/he/events/%d7%90%d7%99%d7%a8%d7%95%d7 %a2-%d7%a1%d7%99%d7%95%d7%9d-%d7%a4%d7%a8%d7%95%d7%99%d7%99%d7%a7%d7%98%d7 %99-%d7%94%d7%92%d7%9e%d7%a8-7-8/ SUMMARY:אירוע סיום פרוייקטי הגמר (7-8) DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:הטכניון - מכון טכנולוגי לישראל\n Location:לובי בניין הפקולטה (הפיטריי ה)\n Zoom: \n Abstract: \n\nשמחים להזמינך לאירוע סיו ם פרוייקטי הגמר (7-8) של הסטודנטים להסמכה ב פקולטה להנדסת אוירונוטיקה וחלל.\n\nיום חמ ישי הקרוב\, 22.8.2024  |  בין השעות 14:30-16:30  |  ב לובי הפקולטה (חלל הפטרייה).\n\nבאירוע יוצג ו 13 פרוייקטי גמר של הסטודנטים בליווי הסב רים\, פוסטרים\, מצגות ודגמים.\n Details: \n CATEGORIES:אירועים LOCATION:לובי בניין הפקולטה (הפיטרייה) END:VEVENT BEGIN:VEVENT UID:0-1378@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240826T013000 DTEND;TZID=Asia/Jerusalem:20240826T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-08-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1379@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240828T013000 DTEND;TZID=Asia/Jerusalem:20240828T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-08-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1380@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240902T013000 DTEND;TZID=Asia/Jerusalem:20240902T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1381@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240904T013000 DTEND;TZID=Asia/Jerusalem:20240904T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1382@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240909T013000 DTEND;TZID=Asia/Jerusalem:20240909T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1383@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240911T013000 DTEND;TZID=Asia/Jerusalem:20240911T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1384@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240916T013000 DTEND;TZID=Asia/Jerusalem:20240916T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1385@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240918T013000 DTEND;TZID=Asia/Jerusalem:20240918T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-824@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240918T193000 DTEND;TZID=Asia/Jerusalem:20240918T210000 DTSTAMP:20240918T145305Z URL:https://aerospace.technion.ac.il/he/events/%d7%98%d7%a7%d7%a1-%d7%a1%d 7%99%d7%95%d7%9d-%d7%aa%d7%95%d7%90%d7%a8-%d7%9e%d7%92%d7%99%d7%a1%d7%98%d 7%a8-2024/ SUMMARY:טקס סיום תואר מגיסטר - 2024 DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:הטכניון - מכון טכנולוגי לישראל\n Location:אודיטוריום 235 - הפקולטה להנ דסת אוירונוטיקה וחלל\n Zoom: \n Abstract: \n\n \;\n\ nהכניסה לאירוע למוזמנים בלבד\n Details: \n CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-823@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240918T193000 DTEND;TZID=Asia/Jerusalem:20240918T210000 DTSTAMP:20240918T145328Z URL:https://aerospace.technion.ac.il/events/masters-graduation-ceremony-20 24/ SUMMARY:Master's Graduation Ceremony 2024 DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Auditorium 235 \, The Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: \n \n \;\n\nEntry to the event is for invitees only\n Details: \n CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1386@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240923T013000 DTEND;TZID=Asia/Jerusalem:20240923T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1387@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240925T013000 DTEND;TZID=Asia/Jerusalem:20240925T023000 DTSTAMP:20251118T063911Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1388@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20240930T013000 DTEND;TZID=Asia/Jerusalem:20240930T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-09-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1389@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241002T013000 DTEND;TZID=Asia/Jerusalem:20241002T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1390@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241007T013000 DTEND;TZID=Asia/Jerusalem:20241007T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1391@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241009T013000 DTEND;TZID=Asia/Jerusalem:20241009T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1392@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241014T013000 DTEND;TZID=Asia/Jerusalem:20241014T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1393@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241016T013000 DTEND;TZID=Asia/Jerusalem:20241016T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1394@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241021T013000 DTEND;TZID=Asia/Jerusalem:20241021T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1395@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241023T013000 DTEND;TZID=Asia/Jerusalem:20241023T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1396@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241028T013000 DTEND;TZID=Asia/Jerusalem:20241028T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1397@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241030T013000 DTEND;TZID=Asia/Jerusalem:20241030T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-10-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1398@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241104T013000 DTEND;TZID=Asia/Jerusalem:20241104T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-11-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1399@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241106T013000 DTEND;TZID=Asia/Jerusalem:20241106T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-11-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1400@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241111T013000 DTEND;TZID=Asia/Jerusalem:20241111T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-11-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1401@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241113T013000 DTEND;TZID=Asia/Jerusalem:20241113T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-11-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1402@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241118T013000 DTEND;TZID=Asia/Jerusalem:20241118T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-11-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1403@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241120T013000 DTEND;TZID=Asia/Jerusalem:20241120T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-11-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1404@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241125T013000 DTEND;TZID=Asia/Jerusalem:20241125T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-11-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1405@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241127T013000 DTEND;TZID=Asia/Jerusalem:20241127T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-11-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1406@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241202T013000 DTEND;TZID=Asia/Jerusalem:20241202T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1407@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241204T013000 DTEND;TZID=Asia/Jerusalem:20241204T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1408@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241209T013000 DTEND;TZID=Asia/Jerusalem:20241209T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1409@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241211T013000 DTEND;TZID=Asia/Jerusalem:20241211T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1410@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241216T013000 DTEND;TZID=Asia/Jerusalem:20241216T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-806@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241216T133000 DTEND;TZID=Asia/Jerusalem:20241216T143000 DTSTAMP:20241216T104038Z URL:https://aerospace.technion.ac.il/events/space-and-satellite-administra tion-at-the-israeli-ministry-of-defense-challenges-opportunities-and-roadm ap/ SUMMARY:Space and Satellite Administration at the Israeli Ministry of Defen se: Challenges\, Opportunities and Roadmap DESCRIPTION:Lecturer:Avi Berger\n Faculty:Department of Aerospace Engineeri ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \ n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1411@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241218T013000 DTEND;TZID=Asia/Jerusalem:20241218T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1412@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241223T013000 DTEND;TZID=Asia/Jerusalem:20241223T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1413@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241225T013000 DTEND;TZID=Asia/Jerusalem:20241225T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1414@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20241230T013000 DTEND;TZID=Asia/Jerusalem:20241230T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2024-12-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1415@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250101T013000 DTEND;TZID=Asia/Jerusalem:20250101T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1416@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250106T013000 DTEND;TZID=Asia/Jerusalem:20250106T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1417@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250108T013000 DTEND;TZID=Asia/Jerusalem:20250108T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1418@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250113T013000 DTEND;TZID=Asia/Jerusalem:20250113T023000 DTSTAMP:20251118T063910Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1419@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250115T013000 DTEND;TZID=Asia/Jerusalem:20250115T023000 DTSTAMP:20251118T063909Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1420@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250120T013000 DTEND;TZID=Asia/Jerusalem:20250120T023000 DTSTAMP:20251118T063909Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1421@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250122T013000 DTEND;TZID=Asia/Jerusalem:20250122T023000 DTSTAMP:20251118T063909Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1422@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250127T013000 DTEND;TZID=Asia/Jerusalem:20250127T023000 DTSTAMP:20251118T063909Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1423@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250129T013000 DTEND;TZID=Asia/Jerusalem:20250129T023000 DTSTAMP:20251118T063909Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-01-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1424@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250203T013000 DTEND;TZID=Asia/Jerusalem:20250203T023000 DTSTAMP:20251118T063909Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-02-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1425@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250205T013000 DTEND;TZID=Asia/Jerusalem:20250205T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-02-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1426@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250210T013000 DTEND;TZID=Asia/Jerusalem:20250210T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-02-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1427@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250212T013000 DTEND;TZID=Asia/Jerusalem:20250212T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-02-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1428@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250217T013000 DTEND;TZID=Asia/Jerusalem:20250217T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-02-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1429@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250219T013000 DTEND;TZID=Asia/Jerusalem:20250219T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-02-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1430@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250224T013000 DTEND;TZID=Asia/Jerusalem:20250224T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-02-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1431@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250226T013000 DTEND;TZID=Asia/Jerusalem:20250226T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-02-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1432@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250303T013000 DTEND;TZID=Asia/Jerusalem:20250303T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1433@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250305T013000 DTEND;TZID=Asia/Jerusalem:20250305T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1434@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250310T013000 DTEND;TZID=Asia/Jerusalem:20250310T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1435@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250312T013000 DTEND;TZID=Asia/Jerusalem:20250312T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1436@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250317T013000 DTEND;TZID=Asia/Jerusalem:20250317T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1437@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250319T013000 DTEND;TZID=Asia/Jerusalem:20250319T023000 DTSTAMP:20251118T063844Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1153@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250319T131500 DTEND;TZID=Asia/Jerusalem:20250319T143000 DTSTAMP:20250209T083923Z URL:https://aerospace.technion.ac.il/events/the-meir-hanin-awards-ceremony -and-seminar/ SUMMARY:The Meir Hanin Awards Ceremony and Seminar DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Auditorium 235\, t he Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: The Me ir Hanin Awards Ceremony:\n\n The Meir Hanin International Aerospace Priz e awardee: Prof. Wei Shyy\n The Meir Hanin Young Researchers scholarships awardees:\n\n Assistant Professor Alexandros Terzis – Aerospace Engine ering Faculty Member\n Joel Van-Der-Lee\, PhD student\n\n\n\nThe ceremony will be followed by a seminar by Prof. Wei Shyy\, winner of the Internati onal Hanin Award.\nSeminar Titel: Low Reynolds number flight vehicles: sca ling and aerodynamics\n\nAbstract: Some of the most interesting areas in a erospace science and technologies are on either higher\, faster and larger systems or lower\, slower and smaller flying capabilities. In this talk\, recent efforts in developing small\, fixed and flapping wing flight vehic les are discussed. As the vehicle sizes vary\, non-proportional scaling be tween areas and weight\, and\, accordingly\, shifting dominance of physica l mechanisms create different operating parameters and technical requireme nts. In this seminar\, examples drawn from both canonical cases as well as developed flight vehicles will be presented. Unsteady aerodynamics via wi ng motion and softer materials under uncertain flight environments are som e of the main focus of the talk.\n\nAbout Professor Wei Shyy:\nProfessor W ei Shyy is a Chair Professor at the Hong Kong University of Science and Te chnology (Guangzhou). He was President of the Hong Kong University of Scie nce and Technology and Chair Professor of Mechanical and Aerospace Enginee ring. Prior to joining HKUST in 2010\, he was Clarence L. “Kelly” John son Collegiate Professor and Chairman of the Department of Aerospace Engin eering of the University of Michigan.\nHe was the Principal Investigator o f several multi-institutional research projects\, funded by the US Governm ent and industries\, on future space transport\, bio-inspired flight\, and computational aero-science. He is General Editor of the Cambridge Aerospa ce Book Series published by the Cambridge University Press\; and Co-Editor -in-Chief of Encyclopedia of Aerospace Engineering\, a major reference wor k published by Wiley-Blackwell.\n\nProfessor Shyy is an elected member of Academia Sinica (Taipei)\, an agenda contributor of the World Economic For um\, and Fellow of the American Institute of Aeronautics and Astronautics (AIAA). He has received awards for his research and professional contribut ions\, including the AIAA 2003 Pendray Aerospace Literature Award\, the AS ME 2005 Heat Transfer Memorial Award\, and The Engineers’ Council (Sherm an Oaks\, CA) 2009 Distinguished Educator Award. In 2021\, the French Gove rnment made him an Officer of the Legion of Honor. In 2023\, the Internati onal Conference on Computational &\; Experimental Engineering and Scien ces (ICCES) honored him the Satya N. Atluri Award.\n\n \;\n Details: \ n CATEGORIES:Seminars LOCATION:Auditorium 235\, the Faculty of Aerospace Engineering\, Technion X-APPLE-STRUCTURED-LOCATION;VALUE=URI;X-ADDRESS=The Faculty of Aerospace En gineering\, the Technion\, Haifa\, Israel;X-APPLE-RADIUS=100;X-TITLE=Audit orium 235:geo:0,0 END:VEVENT BEGIN:VEVENT UID:0-1147@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250320T090000 DTEND;TZID=Asia/Jerusalem:20250320T170000 DTSTAMP:20241205T071801Z URL:https://aerospace.technion.ac.il/events/iacas-2025/ SUMMARY:IACAS 2025 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Technion – Israe l Institute of Technology\n Zoom: \n Abstract: The 64th Israel Annual Conf erence on Aerospace Sciences\, spanning several generations\, is an import ant annual event on the calendar of the aerospace community in Israel and arouses great interest abroad. In this yearly event are engineers\, scient ists\, and experts in the field of aeronautics and astronautics\, represen ting well-known local aerospace agencies and industries and participants f rom major research centers worldwide.\n\nCheck out the IACAS website at:  https://iacas.technion.ac.il/\n\n\n Details: \n CATEGORIES:Events LOCATION:Technion – Israel Institute of Technology END:VEVENT BEGIN:VEVENT UID:0-1148@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250320T090000 DTEND;TZID=Asia/Jerusalem:20250320T170000 DTSTAMP:20241205T074119Z URL:https://aerospace.technion.ac.il/he/events/iacas-2025/ SUMMARY:IACAS 2025 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:הטהטכניון - מכון טכנולוגי לישראל\n Zoom: \n Abstract: הכנס ה ישראלי השנתי ה-64  למדעי התעופה והחלל הוא האירוע השנתי החשוב בלוח השנה של קהילת הת עופה והחלל בישראל ומעורר עניין רב גם בחו" ל. באירוע לוקחים חלק מהנדסים\, מדענים ומו מחים בתחום האווירונאוטיקה והאסטרונאוטי קה\, המייצגים סוכנויות ותעשיות תעופה וחל ל מקומיות\, כמו גם משתתפים ממרכזי מחקר גד ולים ברחבי העולם.\n\nכל הפרטים באתר הכנס: h ttps://iacas.technion.ac.il/\n\n \;\n\n\n Details: \n CATEGORIES:אירועים LOCATION:הטהטכניון - מכון טכנולוגי לישראל END:VEVENT BEGIN:VEVENT UID:0-1438@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250324T013000 DTEND;TZID=Asia/Jerusalem:20250324T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1439@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250326T013000 DTEND;TZID=Asia/Jerusalem:20250326T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1440@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250331T013000 DTEND;TZID=Asia/Jerusalem:20250331T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-03-31/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1441@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250402T013000 DTEND;TZID=Asia/Jerusalem:20250402T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1442@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250407T013000 DTEND;TZID=Asia/Jerusalem:20250407T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-821@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250408T150000 DTEND;TZID=Asia/Jerusalem:20250408T170000 DTSTAMP:20250326T055414Z URL:https://aerospace.technion.ac.il/events/graduation-ceremony/ SUMMARY:Graduation Ceremony DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty yard\n Zoom: \n Abstract: \n\nEntry to the event is for invitees only\n Details: \n\nEntry to the event is for invitees only\n CATEGORIES:Events LOCATION:Faculty yard END:VEVENT BEGIN:VEVENT UID:0-822@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250408T150000 DTEND;TZID=Asia/Jerusalem:20250408T170000 DTSTAMP:20250326T055451Z URL:https://aerospace.technion.ac.il/he/events/%d7%98%d7%a7%d7%a1-%d7%94%d 7%a1%d7%9e%d7%9b%d7%94-%d7%9e%d7%97%d7%96%d7%95%d7%a8-%d7%a1%d7%95/ SUMMARY:טקס הסמכה - מחזור ס"ו DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:הטכניון - מכון טכנולוגי לישראל\n Location:מדשאת הפקולטה\n Zoom: \n Abstract: \n אירוע סגור למוזמנים בלבד\n Details: \n CATEGORIES:אירועים LOCATION:מדשאת הפקולטה END:VEVENT BEGIN:VEVENT UID:0-1154@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250409T003000 DTEND;TZID=Asia/Jerusalem:20250409T023000 DTSTAMP:20250302T134738Z URL:https://aerospace.technion.ac.il/events/iai-spotlight-day/ SUMMARY:IAI "Spotlight Day" DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Faculty yard and A uditorium 235\n Zoom: \n Abstract: \n Details: \n CATEGORIES:Events LOCATION:Faculty yard and Auditorium 235 END:VEVENT BEGIN:VEVENT UID:0-1443@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250409T013000 DTEND;TZID=Asia/Jerusalem:20250409T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1155@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250409T123000 DTEND;TZID=Asia/Jerusalem:20250409T143000 DTSTAMP:20250302T135334Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%96%d 7%a8%d7%a7%d7%95%d7%a8-%d7%94%d7%aa%d7%a2%d7%a9%d7%99%d7%99%d7%94-%d7%94%d 7%90%d7%95%d7%95%d7%99%d7%a8%d7%99%d7%aa-%d7%9c%d7%99%d7%a9%d7%a8%d7%90%d7 %9c/ SUMMARY:יום זרקור - התעשייה האווירית לישראל DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:חצר הפקול טה ואודיטוריום 235\n Zoom: \n Abstract: \n Details: \n יום זרקור - חשיפה לפעילות התעשייה האווירית ו לאשרויות ההשתלבות והתעסוקה לחברה. מיועד לכל הסטודנטים בפקולטה ומכוון ללומדים לת ואר ראשון ולתארים מתקדמים.\n\nנציגי החברה המקצועיים כמו גם נציגי משאבי אנוש יגיעו להפנינג ברחבת הפקולטה ובאודיטוריום\n\n CATEGORIES:אירועים LOCATION:חצר הפקולטה ואודיטוריום 235 END:VEVENT BEGIN:VEVENT UID:0-1444@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250414T013000 DTEND;TZID=Asia/Jerusalem:20250414T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1445@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250416T013000 DTEND;TZID=Asia/Jerusalem:20250416T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1446@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250421T013000 DTEND;TZID=Asia/Jerusalem:20250421T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1447@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250423T013000 DTEND;TZID=Asia/Jerusalem:20250423T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1448@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250428T013000 DTEND;TZID=Asia/Jerusalem:20250428T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1449@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250430T013000 DTEND;TZID=Asia/Jerusalem:20250430T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-04-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1450@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250505T013000 DTEND;TZID=Asia/Jerusalem:20250505T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-05-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1451@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250507T013000 DTEND;TZID=Asia/Jerusalem:20250507T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-05-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1149@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250508T173000 DTEND;TZID=Asia/Jerusalem:20250508T190000 DTSTAMP:20250508T115006Z URL:https://aerospace.technion.ac.il/events/excellence-awards-ceremony-2/ SUMMARY:Excellence Awards Ceremony DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Dan Kahn Building\ , Mechanical Eng. - Auditorium\n Zoom: \n Abstract: Excellence Awards Cere mony for students and faculty\, winter and spring 2023-2024\n\n\n\nThis is an invitation-only event\n Details: \n CATEGORIES:Events LOCATION:Dan Kahn Building\, Mechanical Eng. - Auditorium END:VEVENT BEGIN:VEVENT UID:0-1150@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250508T173000 DTEND;TZID=Asia/Jerusalem:20250508T190000 DTSTAMP:20250508T114951Z URL:https://aerospace.technion.ac.il/he/events/%d7%98%d7%a7%d7%a1-%d7%a4%d 7%a8%d7%a1%d7%99-%d7%94%d7%a6%d7%98%d7%99%d7%99%d7%a0%d7%95%d7%aa-2/ SUMMARY:טקס פרסי הצטיינות DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:אודיטוריו ם בניין דן קאהן\, הפקולטה להנדסת מכונות\n Z oom: \n Abstract: טקס הענקת תעודות הצטיינות דיקנ ית והצטיינות נשיא לסטודנטים\, סמסטרים חו רף ואביב תשפ"ד\n\n\n\nהאירוע למוזמנים בלבד\n\ n \;\n Details: \n CATEGORIES:אירועים LOCATION:אודיטוריום בניין דן קאהן\, הפקולטה ל הנדסת מכונות END:VEVENT BEGIN:VEVENT UID:0-1452@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250512T013000 DTEND;TZID=Asia/Jerusalem:20250512T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-05-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1453@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250514T013000 DTEND;TZID=Asia/Jerusalem:20250514T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-05-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1454@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250519T013000 DTEND;TZID=Asia/Jerusalem:20250519T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-05-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1455@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250521T013000 DTEND;TZID=Asia/Jerusalem:20250521T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-05-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1456@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250526T013000 DTEND;TZID=Asia/Jerusalem:20250526T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-05-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1166@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250528T000000 DTEND;TZID=Asia/Jerusalem:20250528T000000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/open-seminar-slot/ SUMMARY:Open seminar Slot DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:\n Zoom: \n Ab stract: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1457@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250528T013000 DTEND;TZID=Asia/Jerusalem:20250528T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-05-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1458@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250602T013000 DTEND;TZID=Asia/Jerusalem:20250602T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1459@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250604T013000 DTEND;TZID=Asia/Jerusalem:20250604T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1164@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250604T123000 DTEND;TZID=Asia/Jerusalem:20250604T133000 DTSTAMP:20250518T081436Z URL:https://aerospace.technion.ac.il/events/mean-field-population-balance- equations-for-ganglia-dynamics-in-porous-media-models/ SUMMARY:Mean-field population balance equations for ganglia dynamics in por ous media models DESCRIPTION:Lecturer:Dr. Andreas Yiotis \n Faculty:\n Institute:Technical U niversity of Crete\, Greece\n Location:Classroom 165\, ground floor\, Libr ary\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/93899557822\n Abst ract: We study experimentally the dynamics of non-wetting ganglia flowing simultaneously with a wetting fluid in a quasi-two-dimensional porous medi um consisting of random obstacles. The ganglia continuously merge\, formin g larger ones (coalescence)\, and break up into smaller ones (fragmentatio n)\, leading to an overall dynamic equilibrium between the two processes o ver longer time scales. We develop a clustering algorithm for the identifi cation of fragmentation and coalescence events that records the size of ga nglia prior to and immediately after each event from high-resolution video s of the immiscible flow experiments. The results provide significant insi ght into the main physical features of these two processes\, such as gangl ia size distributions\, breakup and coalescence frequency as a function of total flow rate\, and the size distributions of the ganglia formed by eit her the fragmentation or coalescence of other ones. One of the salient fea tures of the fragmentation process in our study is that ganglia that are s maller than the typical pore size exhibit a higher probability of producin g two almost identical children (in size)\, whereas larger ganglia break u p into two children of different sizes. In the latter case\, one of the ch ildren is found to have a dimension that is practically equal to the typic al pore size. Our experimental results are also interpreted in the framewo rk of a mean-field approach\, where the dynamics of the ganglia sizes is e xpressed through an integro-differential population balance equation that comprises terms for the description of the rates of size gains and losses by either fragmentation or coalescence. We recover appropriate expressions for the relevant coalescence and fragmentation kernels\, as functions of the ganglia sizes that participate in each event. A rather surprising resu lt is that for a given ganglion size population\, we obtain an equilibrium between the gains by fragmentation and the losses by coalescence. Further more\, the opposite is also true\, as the population gains by coalescence are found to be equal to the losses by fragmentation.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. X-APPLE-STRUCTURED-LOCATION;VALUE=URI;X-ADDRESS=Classroom 165\, ground floo r\, Library\, Aerospace Eng.\, Haifa\, ;X-APPLE-RADIUS=100;X-TITLE=:geo:0, 0 END:VEVENT BEGIN:VEVENT UID:0-1460@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250609T013000 DTEND;TZID=Asia/Jerusalem:20250609T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1461@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250611T013000 DTEND;TZID=Asia/Jerusalem:20250611T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1167@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250611T123000 DTEND;TZID=Asia/Jerusalem:20250611T143000 DTSTAMP:20250513T125227Z URL:https://aerospace.technion.ac.il/events/faculty-picnic-2025/ SUMMARY:Faculty Picnic 2025 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Faculty yard\n Zoo m: \n Abstract: Faculty of Aerospace Engineering students and staff are al l invited to the coolest event of the year: THE FACULTY PICNIC\n\n\n Detai ls: \n Faculty of Aerospace Engineering students and staff are all invited to the coolest event of the year: THE FACULTY PICNIC CATEGORIES:Events LOCATION:Faculty yard END:VEVENT BEGIN:VEVENT UID:0-1168@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250611T123000 DTEND;TZID=Asia/Jerusalem:20250611T143000 DTSTAMP:20250513T125444Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%a4%d7%99%d7%a7%d7 %a0%d7%99%d7%a7-%d7%94%d7%a4%d7%a7%d7%95%d7%9c%d7%98%d7%99-%d7%94%d7%a9%d7 %a0%d7%aa%d7%99-2025/ SUMMARY:הפיקניק הפקולטי השנתי 2025 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:מדשאת הפק ולטה\n Zoom: \n Abstract: האירוע הכי משפחתי שיש. ה פיקניק הפקולטי השנתי. סטודנטים וסגל הפקו לטה מוזמנים להנות.\n\n\n Details: \n האירוע הכי מ שפחתי שיש. הפיקניק הפקולטי השנתי. סטודנט ים וסגל הפקולטה מוזמנים להנות. CATEGORIES:אירועים LOCATION:מדשאת הפקולטה END:VEVENT BEGIN:VEVENT UID:0-1462@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250616T013000 DTEND;TZID=Asia/Jerusalem:20250616T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1463@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250618T013000 DTEND;TZID=Asia/Jerusalem:20250618T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1464@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250623T013000 DTEND;TZID=Asia/Jerusalem:20250623T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1465@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250625T013000 DTEND;TZID=Asia/Jerusalem:20250625T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1466@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250630T013000 DTEND;TZID=Asia/Jerusalem:20250630T023000 DTSTAMP:20251118T063843Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-06-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1171@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250630T130000 DTEND;TZID=Asia/Jerusalem:20250630T140000 DTSTAMP:20250609T111024Z URL:https://aerospace.technion.ac.il/events/mesoscopic-crystal-plasticity- and-more-modeling-computing-sensing-for-aerospace-applications/ SUMMARY:Mesoscopic crystal plasticity and more – modeling\, computing &am p\; sensing for aerospace applications DESCRIPTION:Lecturer:Dr. Nathan Perchikov\n Faculty:Faculty of Mechanical E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https: //technion.zoom.us/j/93899557822\n Abstract: This seminar presents ongoing research dedicated to the development of physical models\, computational methods and sensor concepts useful for aerospace materials and structures. It gives an overview of several sensing technologies designed to detect e .g. electrostatic-field nonuniformities\, hazardous gas concentrations\, m echanical motion/position-changes\, fatigue-related damage in metals\, flu id viscosity\, etc.\nThe outlined sensor concepts are designed based on dy namical systems theory\, multiphysical models and specialized numerical me thods for discrete- and continuum-mechanics problems — some examples bei ng finite-element and spectral solvers for PDEs\, order-reduction and moda l decomposition methods for ODEs\, etc.\nA detailed discussion is given on the recently developed automaton-form-based mesoscopic theory of crystal plasticity. A hybrid smooth–nonsmooth formulation is introduced\, which models plastic deformation as a quantized process\, enabling the numerical derivation of experimentally observed critical exponents. This approach a llows the simulation of intermittent plasticity with computational speedup of 1-2 orders of magnitude compared to previous formulations.\nWhile micr oscopic theories (e.g. DDD/CDD) resolve atomic-scale patterns in plastic d eformation of real crystalline materials\, they are computationally limite d to small\, sub-structural systems. Macroscopic theories\, in contrast\, being computationally efficient for large-scale systems\, lack fundamental rigor\, often relying on phenomenology.\nThe proposed mesoscopic approach constitutes a viable trade off\, with potential applications in modeling crystalline ice buildup on airplanes\, sensing fatigue-related damage in m etal engine parts/landing-gear components\, designing motion-detection dev ices based on controlled deformation in microcrystals\, etc. In addition\, the theory gives a coarse-graining methodology useful for high-performanc e computing of continua under rapid loading relevant e.g. for modeling of bird strike on aircraft.\n Details: \n CATEGORIES:Seminars LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. X-APPLE-STRUCTURED-LOCATION;VALUE=URI;X-ADDRESS=Classroom 165\, ground floo r\, Library\, Aerospace Eng.\, Haifa\, ;X-APPLE-RADIUS=100;X-TITLE=:geo:0, 0 END:VEVENT BEGIN:VEVENT UID:0-1467@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250702T013000 DTEND;TZID=Asia/Jerusalem:20250702T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1468@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250707T013000 DTEND;TZID=Asia/Jerusalem:20250707T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1469@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250709T013000 DTEND;TZID=Asia/Jerusalem:20250709T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1174@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250710T180000 DTEND;TZID=Asia/Jerusalem:20250710T200000 DTSTAMP:20250708T052254Z URL:https://aerospace.technion.ac.il/events/final-project-presentation-eve nt/ SUMMARY:Final project presentation event DESCRIPTION:Lecturer:\n Faculty:The Stephen B. Klein Faculty of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Faculty yard\n Zoom: \n Abstract: \n\nTen groups will present the prog ress and results of their projects.\nThe projects are mainly guided by the industry. The graduation event summarizes a strenuous and challenging yea r during which each group advances a complex project.\n\n \;\n\n\n Det ails: \n Final project presentation event. CATEGORIES:Events LOCATION:Faculty yard END:VEVENT BEGIN:VEVENT UID:0-1175@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250710T180000 DTEND;TZID=Asia/Jerusalem:20250710T200000 DTSTAMP:20250708T052741Z URL:https://aerospace.technion.ac.il/he/events/%d7%90%d7%99%d7%a8%d7%95%d7 %a2-%d7%a1%d7%99%d7%95%d7%9d-%d7%a4%d7%a8%d7%95%d7%99%d7%99%d7%a7%d7%98%d7 %99-%d7%94%d7%92%d7%9e%d7%a8/ SUMMARY:אירוע סיום פרוייקטי הגמר DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אווירונ וטיקה וחלל ע"ש סטיבן ב. קליין\n Institute:הטכני ון - מכון טכנולוגי לישראל\n Location:דשא הפקול טה\n Zoom: \n Abstract: עשר עשר קבוצות יציגו את הת קדמות ותוצאות פרויקטי הגמר (פרוייקטי 7-8).\ nהפרויקטים מונחים בעיקר על ידי נציגים מה תעשייה. אירוע הסיום מסכם שנה מאומצת ומאת גרת שבמהלכה כל קבוצה מקדמת פרויקט גמר מו רכב.\n\n\n Details: \n תצוגת פרוייקטי 7-8 של הסטוד נטים להסמכה CATEGORIES:אירועים LOCATION:דשא הפקולטה END:VEVENT BEGIN:VEVENT UID:0-1470@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250714T013000 DTEND;TZID=Asia/Jerusalem:20250714T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1169@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250714T180000 DTEND;TZID=Asia/Jerusalem:20250714T213000 DTSTAMP:20250513T130014Z URL:https://aerospace.technion.ac.il/events/graduation-ceremony-2025/ SUMMARY:Graduation Ceremony 2025 DESCRIPTION:Lecturer:\n Faculty:Department of Aerospace Engineering\n Insti tute:Technion – Israel Institute of Technology\n Location:Faculty yard\n Zoom: \n Abstract: \n\nEntry to the event is for invitees only\n Details: \n CATEGORIES:Events LOCATION:Faculty yard END:VEVENT BEGIN:VEVENT UID:0-1170@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250714T200000 DTEND;TZID=Asia/Jerusalem:20250714T213000 DTSTAMP:20250717T104010Z URL:https://aerospace.technion.ac.il/he/events/%d7%98%d7%a7%d7%a1-%d7%94%d 7%a1%d7%9e%d7%9b%d7%94-%d7%9e%d7%97%d7%96%d7%95%d7%a8-%d7%a1%d7%96/ SUMMARY:טקס הסמכה – מחזור ס"ז DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אוירונו טיקה וחלל\n Institute:הטכניון - מכון טכנולוגי לישראל\n Location:דשא הפקולטה\n Zoom: \n Abstract: לחץ כאן לצפיה בכל התמונות מהאירוע\n \;\n\n\n\n\n\ nאירוע סגור למוזמנים בלבד\n Details: \n CATEGORIES:אירועים LOCATION:דשא הפקולטה END:VEVENT BEGIN:VEVENT UID:0-1471@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250716T013000 DTEND;TZID=Asia/Jerusalem:20250716T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1472@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250721T013000 DTEND;TZID=Asia/Jerusalem:20250721T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1172@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250721T133000 DTEND;TZID=Asia/Jerusalem:20250721T143000 DTSTAMP:20250715T084513Z URL:https://aerospace.technion.ac.il/events/experimental-development-of-ad aptive-cycle-micro-turbofan-engine-ace/ SUMMARY:Experimental development of Adaptive Cycle Micro-Turbofan Engine (A CE) DESCRIPTION:Lecturer:Pavel Kolos\n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://techn ion.zoom.us/j/93549691766\n Abstract: \n\n\nThis talk presents the design\ , development\, and validation of an adaptive cycle micro-turbofan engine\ , converted from a baseline micro-turbojet (AMT Nike)\, for application in unmanned aerial systems. Addressing the performance limitations of micro- turbojets—particularly their inefficiency during low-speed and take-off conditions—this work explores a propulsion architecture capable of adapt ing to different flight regimes.\n\nFollowing a mission-driven literature review\, the methodology includes detailed thermodynamic\, aerodynamic\, a nd mechanical analysis of the adaptive engine concept. Key components such as a custom-designed gearbox\, a newly developed fan\, and a variable byp ass nozzle are introduced. Core engine behavior is assessed using experime ntal data and component maps derived from CFD studies.\n\nDesign-point and off-design performance simulations were conducted using a Python-based th ermodynamic modeling tool developed in-house. These simulations guided the selection of optimal fan parameters and gearbox ratios and enabled perfor mance comparison with conventional configurations.\n\nThe mechanical desig n phase covered the structural layout\, stress analysis\, thermal fit desi gn\, and additive manufacturing strategies. Custom assembly and alignment techniques were implemented to ensure mechanical precision and operational reliability.\n\nAn experimental test bench was developed using a real-tim e control system (dSPACE)\, National Instruments hardware\, and a custom S imulink-LabVIEW software environment. Initial tests investigated engine st artup behavior\, sensor performance\, and IDLE regime stability.\n\nThe re sults demonstrate significant improvements in thrust and fuel efficiency u sing the adaptive configuration. The talk concludes with practical insight s from the assembly and testing process\, and recommendations for future e ngine iterations and control system enhancements.\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1473@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250723T013000 DTEND;TZID=Asia/Jerusalem:20250723T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1474@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250728T013000 DTEND;TZID=Asia/Jerusalem:20250728T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1475@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250730T013000 DTEND;TZID=Asia/Jerusalem:20250730T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-07-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1173@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250730T133000 DTEND;TZID=Asia/Jerusalem:20250730T143000 DTSTAMP:20250730T095448Z URL:https://aerospace.technion.ac.il/events/ml-based-wing-shape-loads-and- aoa-sensing-from-measured-strain-from-ground-test-to-flight-ready-integrat ion/ SUMMARY:ML-Based Wing Shape\, Loads\, and AoA Sensing from measured strain: From Ground Test to Flight-Ready Integration DESCRIPTION:Lecturer:Ido Hauzer \n Faculty:Department of Aerospace Engineer ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://techn ion.zoom.us/j/93549691766\n Abstract: \n\n\nThis thesis presents a machine learning (ML) based method for sensing both the shape and applied distrib uted loads of a highly flexible wing (the Pazy wing) using measured strain data. The predicted shape and load distribution are then integrated with an aerodynamic model to estimate the rigid angle of attack (RAoA).\n\nThe research employs a practical approach\, utilizing relatively simple static ground tests with a few concentrated loads to train the ML model\, which subsequently predicts aerodynamic distributed loads and wing deformation d uring wind tunnel tests.\nA comprehensive workflow for designing training experiments and evaluating results is detailed\, complemented by a well-st ructured data processing and training pipeline. The concept is validated u sing ML models initially trained on a finite element (FE) structural model of the wing\, simulating loads that produce geometrically nonlinear defle ctions up to 50% (275mm) of the wing's 550mm span.\nThe performance of the load and shape prediction models is then evaluated using actual wind tunn el test data with deflections up to 100mm\, achieving maximum errors below 9.1%. The generalization and extrapolation capabilities of the models are assessed and demonstrate robust performance beyond the training domain.\n Finally\, the ML models are employed to determine the wing's aerodynamic c haracteristics and estimate the rigid AoA in wind tunnel tests ranging fro m -10° to 10°\, with a maximum error of 5.2% (0.6°) within the model's training range.\nThis study successfully establishes a comprehensive metho dology for predicting in-flight shape and loads using ground-test-trained ML models\, providing an effective approach for estimating RAoA for highly flexible structures.\n\n \;\n\nIdo is a master's student at the Facul ty of Aerospace Engineering at the Technion\, under the supervision of Pro f. Daniela Raveh. He holds a bachelor's degree in Mechanical Engineering f rom the Technion and has over a decade of experience in the aerospace indu stry. His areas of expertise include finite element analysis (FEA)\, multi body dynamics\, experimental testing\, and machine learning. Ido focuses o n integrating simulation\, experimentation\, and advanced algorithms to br idge the gap between physics-based modeling and artificial intelligence\, with the goal of enhancing engineering and validation processes for advanc ed airborne structures.\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1476@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250804T013000 DTEND;TZID=Asia/Jerusalem:20250804T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-08-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1176@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250804T133000 DTEND;TZID=Asia/Jerusalem:20250804T143000 DTSTAMP:20250730T095354Z URL:https://aerospace.technion.ac.il/events/multiscale-analysis-of-interfa ce-driven-momentum-transport-at-free-flow-and-porous-medium-boundaries/ SUMMARY:Multiscale Analysis of Interface-driven Momentum Transport at Free- flow and Porous Medium Boundaries DESCRIPTION:Lecturer:Mario Del Mastro \n Faculty:The Stephen B. Klein Facul ty of Aerospace Engineering\n Institute:Technion – Israel Institute of T echnology\n Location:Classroom 165\, ground floor\, Library\, Aerospace En g.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: \n\n\nThe in teraction between a porous medium and an adjacent free-flow is critical in many natural and engineered systems\, yet accurately describing interfaci al momentum transport remains a challenge. This study examines such couple d systems at the microscale\, using an integrated experimental and theoret ical approach. Soft-lithography-fabricated micromodels and micro-Particle Image Velocimetry (µPIV) are used to characterize momentum transport acro ss the fluid-porous interface under isothermal\, single-phase\, laminar co nditions.\nThe influence of porosity on interfacial slip velocity and boun dary layer development is examined using ordered porous structures. An exp licit analytical solution for interfacial velocity distributions is derive d using the Brinkman model\, overcoming limitations of classical Stokes-ba sed models that suffer from convergence and truncation issues in high widt h-to-height ratio rectangular channels. The developed model incorporates a Navier-type boundary condition and introduces an empirical\, viscosity-in dependent correlation for the slip length\, validated in Hele-Shaw-type fl ows with excellent agreement. Notably\, both slip velocity and slip length increase monotonically with porosity\, highlighting their intrinsic corre lation governed by interfacial momentum transfer mechanisms.\nThe study fu rther extends to disordered porous domains\, providing\, for the first tim e\, two-dimensional velocity field measurements in coupled free-flow and p orous systems with random solid-phase distributions. An asymptotic expansi on method yields a multiscale analytical solution at the Representative El ementary Volume (REV) scale\, resolving both local and averaged dynamics t hrough excess parameter functions that are validated experimentally.\nLast ly\, preliminary results on immiscible two-phase flows lay the groundwork for future multiphase microfluidics in porous systems\, establishing a rob ust experimental pathway for high-resolution imaging and quantitative anal ysis of interfacial dynamics. \;\n\nMario Del Mastro is a PhD candidat e in Aerospace Engineering at the Technion – Israel Institute of Technol ogy\, specializing in experimental and theoretical fluid dynamics at porou s–fluid interfaces. His research integrates microfabrication\, µPIV flo w visualization\, and multiscale modeling of Darcy–Brinkman systems. He has presented at different international conferences such as InterPore2025 and EXHFT10 and was awarded the Jacobs Prize for Excellent Publication in 2025.\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1477@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250806T013000 DTEND;TZID=Asia/Jerusalem:20250806T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-08-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1478@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250811T013000 DTEND;TZID=Asia/Jerusalem:20250811T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-08-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1479@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250813T013000 DTEND;TZID=Asia/Jerusalem:20250813T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-08-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1181@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250813T133000 DTEND;TZID=Asia/Jerusalem:20250813T143000 DTSTAMP:20250805T122054Z URL:https://aerospace.technion.ac.il/events/theoretical-study-of-brownian- particle-diffusion-in-generalized-shear-flows/ SUMMARY:Theoretical Study of Brownian Particle Diffusion in Generalized She ar flows DESCRIPTION:Lecturer:Nan Wang \n Faculty:The Stephen B. Klein Faculty of Ae rospace Engineering at the Technion \n Institute:Technion – Israel Insti tute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aer ospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: Bro wnian particle diffusion in shear flows is of broad scientific and enginee ring interest\, with applications ranging from drug delivery and diffusion -based separation to sedimentation and soot dispersion in aerospace propul sion. In this study\, we present a mathematical framework for predicting t he diffusion of Brownian particles in parallel shear flows. By solving the Langevin equations using stochastic instead of classical calculus\, we pr opose a new mathematical formulation that resolves the particle MSD at all timescales\, both with and without external forcing\, in generalized two- dimensional parallel shear flow.\nIn the absence of constant forcing\, we observe three main stages in the evolution of particle diffusion for Couet te and plane Poiseuille flows\, and four main stages for a polynomial appr oximation of a hyperbolic tangent flow. The particle MSD is distinctly dif ferent across these stages due to different dominant physical mechanisms. In the presence of constant forcing\, the analysis reveals that the influe nce of the external body force emerges at long timescales and is primarily dependent on the flow velocity gradient. Notably\, the variance of partic le displacement undergoes a decline followed by a rise when particles are drifted crossing the region where the velocity gradient reverses sign.\nFo r unsteady flows\, we investigate the particle diffusion in time-periodic shear flows under the influence of a constant forcing in the transverse di rection. The results further demonstrate that particle diffusion in the st reamwise direction is markedly enhanced due to the combined effects of Bro wnian motion in the transverse direction\, the forcing term\, and flow vel ocity gradients.\n\n \;\n\nNan Wang is a Ph.D. candidate under the sup ervision of Professor Yuval Dagan in the faculty of Aerospace Engineering. Her research focuses on the theoretical investigation of Brownian particl e diffusion in shear flows.\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1480@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250818T013000 DTEND;TZID=Asia/Jerusalem:20250818T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-08-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1481@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250820T013000 DTEND;TZID=Asia/Jerusalem:20250820T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-08-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1482@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250825T013000 DTEND;TZID=Asia/Jerusalem:20250825T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-08-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1177@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250825T133000 DTEND;TZID=Asia/Jerusalem:20250825T143000 DTSTAMP:20250813T093808Z URL:https://aerospace.technion.ac.il/events/hydrogen-generation-from-water -and-aluminum-with-different-additives/ SUMMARY:Hydrogen Generation from Aluminum - Water Reaction Using Powder &am p\; Tablets with Different Additives DESCRIPTION:Lecturer:Elinor Kostjukovsky \n Faculty:The Stephen B. Klein Fa culty of Aerospace Engineering at the Technion \n Institute:Technion – I srael Institute of Technology\n Location:Classroom 165\, ground floor\, Li brary\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n Ab stract: \n\n\nHydrogen is one of the most environmentally friendly alterna tive fuels\, releasing only water or water vapor upon oxidation and offeri ng high energy density. However\, storage and transport challenges limit i ts widespread use. A promising solution is on-demand hydrogen generation v ia the reaction between aluminum and water:\nAl+3H_2 O→Al(OH)_3+3/2 H_2\ nThis reaction is hindered under normal conditions due to a passivating ox ide layer on aluminum. In previous research\, a patented thermal-chemical method from the Fine Rocket Propulsion Center consisting of depositing 2.5 % LiH on the aluminum surfaces\, was used to activate the aluminum and ove rcome the oxide barrier.\nThe objective of this study was to see the role of LiH and other less expensive and readily available catalyzing additives (e.g.\, Ca(OH)2 and NaOH) in the reaction by mixing with the aluminum par ticles without the activation by deposition process. The significance of p H and molar concentration in facilitating the aluminum-water reaction was investigated. A parametric study varying the reaction temperature and wate r-to-aluminum ratio was conducted for the different catalyzing ingredients . Through these experiments\, we sought identifying the optimal conditions for maximizing hydrogen yield and improving reaction efficiency. In addit ion\, the use of tablets of the same compositions was studied for better f eeding control. We believe that the small amount of the catalyst reacts wi th the oxide layer\, which then exposes the aluminum to react with water e nabling efficiencies close to 100% at appropriate conditions.\n\nElinor Ko stjukovsky is in Silon program\, an accelerated academic-military program in which we complete both our bachelor’s and master’s degrees within f ive years before entering military service. She completed her bachelor's d egree with honors in October 2024 in aerospace engineering and currently p ursuing my master’s degree under the supervision of Professor Alon Gany. \nHer research focuses on on-demand hydrogen generation from aluminum and water.\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1483@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250827T013000 DTEND;TZID=Asia/Jerusalem:20250827T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-08-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1484@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250901T013000 DTEND;TZID=Asia/Jerusalem:20250901T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1185@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250901T133000 DTEND;TZID=Asia/Jerusalem:20250901T143000 DTSTAMP:20250828T063103Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-29-3/ SUMMARY:Preliminary Structural Design Tool for Flexible Slender Bodies with Aeroelastic Constraints DESCRIPTION:Lecturer:Yaara Karniel \n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering at the Technion \n Institute:Technion – Israel Institute of Technology\n Location:Classroom 165\, ground floor\, Library\ , Aerospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract : Slender aerospace vehicles\, such as missiles and rockets\, are inherent ly flexible and therefore deform under aerodynamic loading. With new\, adv anced light-weight materials\, modern designs are becoming increasingly mo re flexible\, making aeroelastic effects a critical factor in performance and stability. For slender bodies\, aerodynamic forces can bend the vehicl e into a characteristic “smiling” shape\, shifting the aerodynamic cen ter of pressure forward and reducing static stability. Remarkably\, even m odest elastic deformations can render an otherwise stable vehicle unstable \, stressing the necessity of accounting for static aeroelastic stability from the earliest design stages.\n\nConventional design methodologies foll ow a hierarchical sequence in which the aerodynamic shape is determined fi rst\, followed by structural design\, which is directed primarily by stres s considerations. Aeroelastic effects\, however\, are often overlooked unt il later phases\, when structural parameters are fixed and design revision s become costly.\n\nThis study presents a novel preliminary design methodo logy that integrates aeroelastic stability analysis at the earliest stage\ , when only the vehicle geometry is available\, and no detailed structural design exists. The proposed framework represents deformations as a combin ation of generalized beam mode shapes\, adapted to capture discontinuities in material and geometry\, along with rigid-body contributions. Aerodynam ic loading is modeled using a potential-flow panel method\, enabling compu tation of the elastically deformed shape and its effect on static stabilit y. Pareto-front analysis connects structural design parameters to overall weight and stability margin\, providing designers with valuable trade-off insight. A Genetic Algorithm–based optimization then identifies structur al configurations that achieve minimum weight while meeting prescribed sta bility requirements.\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1485@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250903T013000 DTEND;TZID=Asia/Jerusalem:20250903T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1486@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250908T013000 DTEND;TZID=Asia/Jerusalem:20250908T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1179@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250908T133000 DTEND;TZID=Asia/Jerusalem:20250908T143000 DTSTAMP:20250831T110952Z URL:https://aerospace.technion.ac.il/events/experimental-investigation-of- a-solid-fuel-ramjet-projectile/ SUMMARY:Experimental Investigation of a Solid Fuel Ramjet Projectile DESCRIPTION:Lecturer:Itamar Levitan\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering\n Institute:Technion – Israel Institute of Tech nology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\ n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: \n\n\nSolid Fue l Ramjet (SFRJ) is considered for active propulsion to increase the range of gun-launched projectiles\, demonstrating high Specific Impulse (Isp)\, natural ability to sustain ballistic (pseudovacuum) trajectory in varying atmospheric conditions\, and to some extent balance wind deviations.\nIn t his work experimental investigation of an SFRJ motor was carried out\, con sidering a 76 mm projectile flying at 930 m/s (Mach 2.73 at sea level) as a reference\, with a fuel grain length of 17 cm without a mixing chamber. Using static firing tests\, different fuels were considered with HTPB and polyester as baseline fuels. For additives we’ve used normal and expanda ble graphite (EG)\, metals such as aluminum and magnesium\, and PTFE (Tefl on).\nIt was found that HTPB-based fuels give substantially higher energet ic performance than polyester. Magnesium and aluminum additives increase t he thrust\, but the latter exhibits lower combustion efficiency. When addi ng PTFE\, aluminized fuel efficiency increases. Expandable graphite additi ves reveal enhanced fuel regression rate by up to 60%\, implying higher th rust. The desired thrust-equal-drag conditions (for a pseudovacuum traject ory) can be approached with an inlet airflow rate of 1.45 kg/s and appropr iate combinations of fuels and additives.\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1158@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250908T190000 DTEND;TZID=Asia/Jerusalem:20250908T210000 DTSTAMP:20250701T134429Z URL:https://aerospace.technion.ac.il/events/masters-graduation-ceremony-20 25/ SUMMARY:Master's Graduation Ceremony 2025 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Auditorium 235\, T he Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: \n Det ails: \n \n\n \;\n\nEntry to the event is for invitees only CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1159@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250908T190000 DTEND;TZID=Asia/Jerusalem:20250908T210000 DTSTAMP:20250701T134446Z URL:https://aerospace.technion.ac.il/he/events/%d7%98%d7%a7%d7%a1-%d7%a1%d 7%99%d7%95%d7%9d-%d7%aa%d7%95%d7%90%d7%a8-%d7%9e%d7%92%d7%99%d7%a1%d7%98%d 7%a8-2025/ SUMMARY:טקס סיום תואר מגיסטר - 2025 DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:אודיטוריו ם 235 - הפקולטה להנדסת אוירונוטיקה וחלל\n Zo om: \n Abstract: \n Details: \n \n\n \;\n\nהכניסה לאירוע למוזמנים בלבד CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1487@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250910T013000 DTEND;TZID=Asia/Jerusalem:20250910T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1488@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250915T013000 DTEND;TZID=Asia/Jerusalem:20250915T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1489@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250917T013000 DTEND;TZID=Asia/Jerusalem:20250917T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1178@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250917T133000 DTEND;TZID=Asia/Jerusalem:20250917T143000 DTSTAMP:20250827T093714Z URL:https://aerospace.technion.ac.il/events/experimental-investigation-of- burning-rate-of-solid-propellants-with-expandable-graphite-additives-at-hi gh-pressures/ SUMMARY:Experimental Investigation of Burning Rate of Solid Propellants wit h Expandable Graphite Additives at High Pressures DESCRIPTION:Lecturer:Noa Hanina \n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering at the Technion \n Institute:Technion – Israel Ins titute of Technology\n Location:Classroom 165\, ground floor\, Library\, A erospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: \ n\n\nThis study examines the enhancement of composite solid propellant bur ning rates by the addition of expandable graphite (EG)\, focusing on high- pressure combustion conditions typical of rocket motors. The burning rate of solid propellants is characteristic to the propellant formulation and i t increases with pressure. Expandable graphite\, a form of graphite interc alated with guest molecules\, expands and elongates into worm-like structu res when heated above approximately 200°C. When incorporated into the pro pellant matrix\, the elongate EG strings can protrude from the burning sur face conducting heat from the hot combustion gases into the unburned mater ial. This enhanced heat feedback accelerates the propellant decomposition process\, leading to a higher burning rate.\nExperiments were conducted us ing a high-pressure\, windowed strand-burner test cell on ammonium perchlo rate (AP)-based propellants with hydroxyl-terminated polybutadiene (HTPB) or polyester binders. Propellant strands were tested with various EG types differing in flake size (100–350 µm) and expansion onset temperature ( 150–240°C)\, at mass fractions ranging from 0 to 5%\, with a constant A P content of 75%. Results showed that EG had a more pronounced effect on A P-HTPB formulations\, achieving up to 35% increase in burning rate at high pressures\, while AP-polyester compositions exhibited a less significant response. In general\, higher EG content led to greater enhancement. These findings demonstrate that EG is an effective additive for improving burni ng rates by enhancing internal heat conduction\, offering a promising appr oach to optimize the performance of solid propellants in high-pressure app lications.\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1184@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250918T133000 DTEND;TZID=Asia/Jerusalem:20250918T143000 DTSTAMP:20250909T072746Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-29-2/ SUMMARY:On Saint-Venant Principle for Carbon Nanotubes DESCRIPTION:Lecturer:Eyal Lerman\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering at the Technion \n Institute:Technion – Israel Ins titute of Technology\n Location:Classroom 165\, ground floor\, Library\, A erospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: \ n\n\nSaint-Venant Principle (SVP)\, a central principle in both elasticity theory and structural mechanics\, states that localized self-equilibratin g loads create stress and strain fields that decay with distance from the loaded region. However\, while well established for macroscopic homogeneou s structures\, its relevance at the nanoscale is less certain. Carbon nano tubes (CNTs)—with their exceptional mechanical properties and slender cy lindrical shape provide a unique framework to examine the validity of SVP for elastic structures at the nanoscale.\nThis research studies the validi ty of SVP in CNTs subjected to localized axial loading. Analysis is within the framework of linear elastic stability theory in conjunction with the nature of nanoscale response. Mathematical models are developed for repres entative configurations such as concentric CNT-like beams embedded in elas tic media\, systems with unequal radii\, and simultaneous buckling of mult ilayer arrangements.\nFindings indicate that localized self-equilibrating loads applied to CNT systems induce axially decaying (exponentially) stres s and strain fields\, though the rate and nature of axial decay depend str ongly on geometry\, constitutive response\, and interlayer interactions. T hese observations suggest that a modified version of SVP applies at the na noscale\, advancing our understanding of stress transfer in nanostructures and paving the way to future research.\n\n\n\n \;\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1490@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250922T013000 DTEND;TZID=Asia/Jerusalem:20250922T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1491@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250924T013000 DTEND;TZID=Asia/Jerusalem:20250924T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1492@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250929T013000 DTEND;TZID=Asia/Jerusalem:20250929T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-09-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1183@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20250929T133000 DTEND;TZID=Asia/Jerusalem:20250929T143000 DTSTAMP:20250916T081303Z URL:https://aerospace.technion.ac.il/events/linear-stability-analysis-of-t he-quasi-one-dimensional-flow-in-a-scramjet-engine/ SUMMARY:Linear Stability Analysis of the Quasi-One-Dimensional Flow in a Sc ramjet Engine DESCRIPTION:Lecturer:Shahaf Haiman \n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering at the Technion \n Institute:Technion – Israel Institute of Technology\n Location:Classroom 165\, ground floor\, Library\ , Aerospace Eng.\n Zoom: https://technion.zoom.us/j/99134371569\n Abstract : \n\n\nThis study presents a linear stability analysis of the flow within a dual-mode scramjet engine. The flow is assumed to be compressible\, inv iscid and quasi-one-dimensional\, and the effects of area variation\, wall friction\, and distributed heat addition are considered. Unlike previous models that rely on asymptotic expansions about zero perturbation frequenc y\, in this work the full linearized quasi-one-dimensional Euler equations are solved. Consequently\, the spatial distributions of the flow disturba nces throughout the entire scramjet domain are obtained and examined. Both modes of scramjet operation are analyzed – scram (supersonic throughout ) and ram (thermally choked with an upstream shock wave)\, in contrast to the traditionally investigated choking due to geometric constraint. The no nlinear base flow\, including the locations of the shock and the effective throat\, is solved using a multi-domain spectral collocation method in co njunction with the shock-fitting approach\, which is also applied to the l inear perturbation equations. The analysis reveals that the energy of entr opy\, fast acoustic\, and slow acoustic disturbances may grow downstream\, particularly in regions of high heat release. Perturbations in the shock position and effective throat location are also quantified.\n\n\n\n Detail s: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1493@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251001T013000 DTEND;TZID=Asia/Jerusalem:20251001T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1494@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251006T013000 DTEND;TZID=Asia/Jerusalem:20251006T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1495@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251008T013000 DTEND;TZID=Asia/Jerusalem:20251008T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1496@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251013T013000 DTEND;TZID=Asia/Jerusalem:20251013T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1497@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251015T013000 DTEND;TZID=Asia/Jerusalem:20251015T023000 DTSTAMP:20251118T063842Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1498@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251020T013000 DTEND;TZID=Asia/Jerusalem:20251020T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1499@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251022T013000 DTEND;TZID=Asia/Jerusalem:20251022T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1500@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251027T013000 DTEND;TZID=Asia/Jerusalem:20251027T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1501@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251029T013000 DTEND;TZID=Asia/Jerusalem:20251029T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1187@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251029T133000 DTEND;TZID=Asia/Jerusalem:20251029T143000 DTSTAMP:20251020T094137Z URL:https://aerospace.technion.ac.il/events/seminar-slot/ SUMMARY:Estimation of Rigid-Body States from the Fusion of Inertial and Str ain Measurements DESCRIPTION:Lecturer:Kay Levinson \n Faculty:The Stephen B. Klein Faculty o f Aerospace Engineering at the Technion \n Institute:Technion – Israel I nstitute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: Modern flight vehicles are becoming increasingly flexible as design trend s drive toward lighter structures and higher aspect ratios for improved ae rodynamic efficiency. In conventional aircraft\, the coupling between flig ht dynamics (rigid-body motion) and the elastic motion is limited\, allowi ng separate analyses of flight dynamics and aeroelasticity (e.g.\, flutter ). However\, for configurations such as flying wings or very flexible airc raft\, this separation breaks down. The elastic and rigid-body dynamics in teract strongly\, and a unified formulation is required to capture their m utual influence. This coupling can be leveraged to estimate the rigid body motion based on its impact on the elastic dynamic response. The study pre sents a combined aeroelastic and flight-dynamic model that integrates drag \, gravity\, and Coriolis effects into the equations of motion. The system is expressed in state-space form using rational function approximation of the unsteady aerodynamics. Building on this formulation\, the second part of the study demonstrates how in-flight measurements of elastic response can be exploited to estimate the vehicle’s rigid-body motion using a Kal man Filter. The method is applied to the A3TB flying-wing testbed\, which experiences body-freedom flutter in flight\, combining the short-period an d elastic bending and torsion modes. Results show that the unified model i mpacts flutter prediction and that the Kalman-based estimator successfully reconstructs rigid-body states from aeroelastic response data. Results hi ghlight the potential for integrated modeling and state estimation in futu re flexible-aircraft systems.\n\n \;\n\n \;\n\n \;\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1502@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251103T013000 DTEND;TZID=Asia/Jerusalem:20251103T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-11-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1503@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251105T013000 DTEND;TZID=Asia/Jerusalem:20251105T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-11-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1189@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251105T123000 DTEND;TZID=Asia/Jerusalem:20251105T143000 DTSTAMP:20251027T132316Z URL:https://aerospace.technion.ac.il/events/winter-semester-2025-2026-open ing-event/ SUMMARY:Winter Semester 2025-2026 - Opening Event DESCRIPTION:Lecturer:\n Faculty:The Stephen B. Klein Faculty of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoo m: \n Abstract: \n Details: \n Event Sponsor: Elbit Systems Ltd.\n\nLectur e: UAV Missions during Iron Swards\n\n CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1190@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251105T123000 DTEND;TZID=Asia/Jerusalem:20251105T143000 DTSTAMP:20251027T132649Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%a4%d7%a0%d7%99%d7 %a0%d7%92-%d7%a4%d7%aa%d7%99%d7%97%d7%aa-%d7%a1%d7%9e%d7%a1%d7%98%d7%a8-%d 7%97%d7%95%d7%a8%d7%a3-%d7%aa%d7%a9%d7%a4%d7%95/ SUMMARY:הפנינג פתיחת סמסטר חורף תשפ"ו DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:אודיטוריו ם 235 - הפקולטה להנדסת אוירונוטיקה וחלל\n Zo om: \n Abstract: \n Details: \n \nאירוע בחסות אלביט מער כות.\n\nהרצאת פתיחה בנושא: כטמ״מ במלחמת חר בות ברזל ועם כלביא.\nמשימות הכטמ״מ בלחימה \, התפתחויות ותמורות תוך כדי לחימה\, הסתכל ות לשנים הבאות.\n\nבסיום ההרצאה: עגלת גליד ה איטלקית\, סוכריות ושוקולד!\n\n\n CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1188@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251105T133000 DTEND;TZID=Asia/Jerusalem:20251105T143000 DTSTAMP:20251019T123915Z URL:https://aerospace.technion.ac.il/events/a-computational-study-of-polyd isperse-particle-laden-turbulent-channel-flows/ SUMMARY:A Computational Study of Polydisperse Particle-laden Turbulent Chan nel Flows DESCRIPTION:Lecturer:Ajay Dhankarghare\n Faculty:Department of Aerospace En gineering\n Institute:Technion – Israel Institute of Technology\n Locati on:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https:/ /technion.zoom.us/j/93549691766\n Abstract: \n\n\nThe introduction of disp ersed particles into a clean flow significantly influences fluid character istics such as turbulent fluctuations\, mass flow rate\, and Reynolds shea r stress. These effects are governed by particle inertia\, mass fraction\, and dispersity. Conventional Lagrangian approaches\, which track individu al particles\, become computationally intensive for large particle numbers . To address this\, we propose a novel Eulerian framework for simulating p olydisperse particles in compressible turbulent flows. This approach resol ves particles as a continuum field using the quadrature-based moment metho d\, enabling the simulation of extremely large number of particles. By two -way coupling this framework with a modified low-dissipation upwind scheme for the gas phase\, we perform Direct Numerical Simulations of turbulent particle-laden channel flows at moderate Reynolds numbers.\n\nOur simulati ons consider different Stokes numbers\, particle mass fractions\, and disp erities. The results show that the method accurately captures key flow phe nomena\, including turbulent statistics\, kinetic energy\, skin friction d rag\, turbophoresis\, interphase momentum exchange\, and particle mass tra nsport. In the near-wall region\, particles tend to cluster in low-speed s treaks\, thereby organizing and modulating fluid turbulence. We further ex tend the framework by introducing a small fraction of secondary particles with different inertia into a monodisperse system. We show that this bidis perse distribution of particles alters the turbulence near the wall but ha s a negligible impact in the channel core. This is attributed to different ial particle migration rates along the channel height. Finally\, the frame work is extended to simulate heat transfer between the fluid and dispersed phases\, demonstrating its broad applicability for multiphase turbulent f lows.\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1504@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251110T013000 DTEND;TZID=Asia/Jerusalem:20251110T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-11-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1186@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251110T133000 DTEND;TZID=Asia/Jerusalem:20251110T143000 DTSTAMP:20251103T115336Z URL:https://aerospace.technion.ac.il/events/geometric-and-operatorial-pers pectives-in-hamiltonian-and-relativistic-dynamics/ SUMMARY:Colloquium: A Talk about Geometric and Operatorial Perspectives in Hamiltonian and Relativistic Dynamics DESCRIPTION:Lecturer:Vladimir Martinusi \n Faculty:The Stephen B. Klein Fac ulty of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Location:Auditorium 235\, The Faculty of Aerospace Engineeri ng\, Technion\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: \ n\nYou are cordially invited to attend the First Aerospace Engineering Col loquium!\n\nThe Colloquium outlines a unified operatorial approach to anal ytical dynamics in which geometric and algebraic structures are treated on equal footing. Beginning with the Jacobi-metric formulation of conservati ve systems\, the Hamiltonian function is re-expressed through an alternati ve Legendre transformation that exposes hidden symmetries and separability patterns. Within this framework\, the Levi-Civita separability condition is formulated as the vanishing of a five-argument operator constructed fro m nested Poisson brackets\, providing a compact criterion for integrabilit y.\n\nThe Deprit triangle of canonical perturbation theory is then interpr eted in terms of Toeplitz-like operator matrices\, clarifying the algebrai c mechanisms underlying canonical reduction. Metric-based quantities such as the Einstein tensor and the Kretschmann scalar are presented as natural geometric invariants within the same operatorial language\, bridging clas sical and relativistic dynamics. Finally\, the framework is connected to a pplied astrodynamical problems through non-drift analytic conditions relev ant to large-aperture satellite formations.\n\nTogether\, these perspectiv es emphasize the emergence of an algebraic differential geometry unifying Hamiltonian theory\, metric geometry\, and operator analysis into a single coherent formalism\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1505@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251112T013000 DTEND;TZID=Asia/Jerusalem:20251112T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-11-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1506@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251117T013000 DTEND;TZID=Asia/Jerusalem:20251117T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-11-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1195@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251118T133000 DTEND;TZID=Asia/Jerusalem:20251118T143000 DTSTAMP:20251117T133804Z URL:https://aerospace.technion.ac.il/events/effect-of-gaps-and-bumps-on-bo undary-layer-transition/ SUMMARY:Effect of gaps and bumps on boundary layer transition DESCRIPTION:Lecturer:Marcello Augusto Faraco de Medeiros\n Faculty:Escola d e Engenharia de São Carlos (EESC)\n Institute:University of São Paulo\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: h ttps://technion.zoom.us/j/93549691766\n Abstract: Transition to turbulence is challenging research with importance to both low and high speed flight vehicle. This seminar will focus on the long standing topic of the effect of surface irregularities on transition\, including the long researched p roblem of bumps and the much less investigated gaps. Despite having been i nvestigated for almost a century\, there are still many open questions abo ut the effect of bumps on transition. The seminar will include low-speed l ow-turbulence wind tunnel experiments\, direct numerical simulations\, loc al/global instability analysis\, advanced signal processing. The talk will cover receptivity\, interaction with TS waves and by pass transition. Mos t of the seminar will focus on the subsonic regime\, but applications to s upersonic regime will also be covered.\n\nProf. Marcello A. Faraco de Mede iros holds a bachelor's degree in Mechanical Engineering from the Federal University of Rio de Janeiro (1987)\, a master's degree in Mechanical Engi neering from the Federal University of Rio de Janeiro (1990)\, and a Ph.D. in Aerospace Engineering from the University of Cambridge (1996). He is a faculty member of the University of São Paulo since 2002\, and was visit ing professor at the Universidad Politecnica de Madrid (2012-2013)\, at th e University of Liverpool (2018-2019) and at Technion\, Israel Institute o f Technology (2025). He has experience in Aerospace Engineering\, with emp hasis on Aerodynamics\, working primarily on the following topics: hydrody namic instability\, boundary layers\, transition\, turbulence\, and aeroac oustics. Among the main applications were natural transition in boundary l ayers and the effect of surface imperfections\, including receptivity\, To llmien-Schlichting waves and by-pass transition\; and slat and cavity nois e. He uses experiments\, theory and numerical simulations and has designed low turbulence wind tunnels and developed codes for numerical simulations \, linear stability analysis and beamforming. He collaborated with the ind ustrial section including Boeing\, SAAB\, American Air Force\, Embraer and Petrobras\, among others. He has received a number of awards (including E mbraer prize of best thesis)\, represents Brazil in a number of organizati ons (among them\, the IUTAM)\, and gave seminars in many institutions and events.\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1507@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251119T013000 DTEND;TZID=Asia/Jerusalem:20251119T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-11-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1197@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251119T133000 DTEND;TZID=Asia/Jerusalem:20251119T143000 DTSTAMP:20251120T072852Z URL:https://aerospace.technion.ac.il/events/bubbly-shock-characterization- in-aerated-cavitating-flow/ SUMMARY:Bubbly Shock Characterization in Aerated Cavitating Flow DESCRIPTION:Lecturer:Elad Zur\n Faculty:The Stephen B. Klein Faculty of Aer ospace Engineering\n Institute:Technion – Israel Institute of Technology \n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom : https://technion.zoom.us/j/93549691766\n Abstract: The complex coupled i nteractions between non-spherical bubbles in cavitation clouds and bubbly shocks present significant challenges for experimental measurements and hi gh-fidelity simulations. Capturing these interactions requires an experime ntal setup with optical access and advanced data-processing capabilities f or simultaneous monitoring of bubbly shocks and bubble dynamics. This stud y addresses these challenges by constructing a dedicated experimental setu p for aerated cavitating flows in a generic converging-diverging (CD) nozz le and utilizing computer vision (CV) tools coupled with the enhanced grad ient shadowgraphy technique for bubbly shock detection and tracking. Our s etup enables the collection of high-speed imaging and high-frequency unste ady pressure measurements to study cavitation phenomena in various liquids and controlled void fractions. We demonstrate the application of our code for the characterization of bubbly shock waves in aerated cavitating flow s in a CD nozzle for different flow liquids\, including distilled water\, dodecane (aviation fuel surrogate)\, and aviation fuel liquids. Using our experimental setup and our processing code for the high-speed imaging\, un precedented quantitative data are obtained on the collapse of attached cav ity clouds in the diverging section of the nozzle at the throat exit\; the spatio-temporal evolution of bubbly shock waves\, emitted from these clou ds\; and on bubbly shock morphology during their interaction with shed vor tical cavities. In the seminar\, a detailed discussion on the differences in cavitation behavior between distilled water and dodecane will be presen ted\, contributing valuable information toward the development of improved models for predicting and controlling cavitation in various internal flow systems.\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1508@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251124T013000 DTEND;TZID=Asia/Jerusalem:20251124T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-11-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1509@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251126T013000 DTEND;TZID=Asia/Jerusalem:20251126T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-11-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1510@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251201T013000 DTEND;TZID=Asia/Jerusalem:20251201T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-12-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1196@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251203T133000 DTEND;TZID=Asia/Jerusalem:20251203T143000 DTSTAMP:20251203T095448Z URL:https://aerospace.technion.ac.il/events/colloquium-a-talk-about-heat-a nd-mass-transfer-phenomena-in-the-free-and-near-free-molecular-flow-regime s/ SUMMARY:Colloquium: A Talk about Heat and Mass Transfer Phenomena in the Fr ee-and Near-Free-Molecular Flow Regimes DESCRIPTION:Lecturer:Assoc. Prof. Avshalom Manela\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering\n Institute:Technion – Israel Ins titute of Technology\n Location:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoom: https://technion.zoom.us/j/93549691766\n Ab stract: \nYou are cordially invited to attend the Second Aerospace Enginee ring Colloquium!\n\nThe Stephen B. Klein Faculty of Aerospace Engineering Colloquium series is a prime stage to spotlight the faculty researchers an d the most up-to-date scientific work our faculty members conduct. On our second Colloquium\, Assoc. Prof. Avshalom Manela will speak at the Aerospa ce Engineering Colloquium about Heat and Mass Transfer Phenomena in the Fr ee-and Near-Free-Molecular Flow Regimes.\nThe analysis of non-continuum ga s flows\, modeled in the framework of gas kinetic theory and associated Bo ltzmann equation\, is a challenging task that commonly requires heavy-load numerical computations. Yet\, seeking more mathematical and physical insi ght\, rigorous investigations are much desirable. To this end\, the free- and near-free-molecular flow regimes\, characterized by high rarefaction r ates\, are relatively convenient to handle. This talk will present some re cent work on this topic\, including problems in acoustics\, microchannel m ass transfer\, and flow detachment. For each problem\, analytical predicti ons will be presented\, accompanied by numerical calculations for validati on.\n Details: \n CATEGORIES:Seminars LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1513@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251210T013000 DTEND;TZID=Asia/Jerusalem:20251210T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-12-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1512@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251210T133000 DTEND;TZID=Asia/Jerusalem:20251210T143000 DTSTAMP:20251204T080129Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-12-08/ SUMMARY:Combustion and Mixing of Liquid Hydrocarbon Fuel in a Scramjet Mode l Combustor DESCRIPTION:Lecturer: Joel van der Lee\n Faculty: The Stephen B. Klein Facu lty of Aerospace Engineering\n Institute:Technion – Israel Institute of Technology\n Location:Classroom 165\, ground floor\, Library\, Aerospace E ng.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: This resear ch work investigates liquid-fueled scramjet combustion and mixing with a f ocus on injection strategy and the development of diagnostics to interroga te mixing fields. Reliable characterization of fuel distribution is crucia l\, as mixing directly governs the ability to stabilize flames in superson ic crossflows.\n\nThe work is divided into two parts. Part I evaluates wal l-based injection relative to strut-assisted injection with a backward-swe pt strut in a cavity-based combustor. Using qualitative filtered infrared imaging and chemiluminescence diagnostics\, the objective was to assess st rut injection as a means of enhancing fuel–air mixing and extending the stability envelope. The results show that strut-assistance promotes latera l dispersion of the plume and enables flame stabilization beyond what can be achieved with conventional wall-based injection upstream of the cavity. \n\nPart II was carried out in an updated combustor configuration and focu ses on the development of a quantitative infrared imaging method tailored to liquid fuels. This approach\, which has not previously been applied to liquid-fueled scramjets\, addresses challenges associated with radiance ab sorption and incomplete vaporization. By employing fuel surrogates at redu ced enthalpy\, time-averaged path density maps were obtained to characteri ze plume penetration\, entrainment into the cavity\, and downstream spread ing across multiple strut injection schemes. These mixing measurements wer e directly related to combustion experiments\, showing how entrainment cha racteristics explain the observed differences in flame holding capability. \n\nTogether\, this work demonstrates a novel application of quantitative infrared diagnostics to liquid-fueled systems and systematically evaluates fueling strategies\, contributing both methodology and physical insight t o the design of advanced liquid-fueled scramjet combustors.\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1624@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251215T133000 DTEND;TZID=Asia/Jerusalem:20251215T143000 DTSTAMP:20251207T065001Z URL:https://aerospace.technion.ac.il/events/bubbly-shock-characterization- in-aerated-cavitating-flow-2/ SUMMARY:Linear Quadratic Powered Descent with Approach Angle Control and Th rust Bounds DESCRIPTION:Lecturer:Or Nataf \n Faculty:The Stephen B. Klein Faculty of Ae rospace Engineering\n Institute:Technion – Israel Institute of Technolog y\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoo m: https://technion.zoom.us/j/93549691766\n Abstract: Space exploration ha s expanded significantly in recent years. The powered descent maneuver use d in planetary landing uses the lander’s rocket engines to guide it to a soft landing at the designated landing site (i.e.\, zero velocity at the target coordinates). The primary challenges in designing guidance laws for a soft landing stem from real-world mission constraints\, like avoiding g round collisions\, controlling approach angles\, and accounting for thrust saturation\, while minimizing fuel consumption.\n\nThe research proposes two different formulations of the problem to address these challenges. The first formulation addresses the approach angle problem and proposes a lin ear-quadratic optimal guidance law with an optimally selected intermediate point. This allows for trajectory shaping and control of the terminal app roach direction. The second formulation uses a time-dependent polynomial a pproximation of the mass consumption to formulate a bounded linear-quadrat ic optimal control problem. The guidance law predicts the entry and exit t imes from the saturation regions and shapes the thrust acceleration profil e to achieve a soft landing while avoiding ground collision. The two guida nce laws are computationally efficient\, and their thrust acceleration pro files are continuous\, facilitating implementation in real-world applicati ons.\n\nThe performance of the two guidance laws is evaluated in simulatio ns. It will be shown that both guidance laws achieve a soft landing with e xcellent performance while maintaining their intended design objectives an d constraints.\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1516@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251222T013000 DTEND;TZID=Asia/Jerusalem:20251222T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-12-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1191@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251224T123000 DTEND;TZID=Asia/Jerusalem:20251224T143000 DTSTAMP:20251106T122759Z URL:https://aerospace.technion.ac.il/events/gvahim-annual-ceremony/ SUMMARY:GVAHIM Annual Ceremony DESCRIPTION:Lecturer:\n Faculty:The Stephen B. Klein Faculty of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoo m: \n Abstract: \n Details: \n We are pleased to invite you to the annual GVAHIM Excellence Program's ceremony.\n\n\n\n Opening remarks: Dr. Yigal Gluzman\, GVAHIM and SILON Programs Coordinator\n Address by the Dean\, P rof. Daniella Raveh\n Lectures by students graduating from the second/thi rd year of the Program\n Introduction of the new students\n Excellence A ward Ceremony\n Lunch\n CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1192@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251224T123000 DTEND;TZID=Asia/Jerusalem:20251224T143000 DTSTAMP:20251106T123743Z URL:https://aerospace.technion.ac.il/he/events/%d7%aa%d7%9b%d7%a0%d7%99%d7 %aa-%d7%92%d7%91%d7%94%d7%99%d7%9d-%d7%94%d7%98%d7%a7%d7%a1-%d7%94%d7%a9%d 7%a0%d7%aa%d7%99/ SUMMARY:תכנית גבהים: הטקס השנתי DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אווירונ וטיקה וחלל ע"ש סטיבן ב. קליין\n Institute:הטכני ון - מכון טכנולוגי לישראל\n Location:אודיטורי ום 235 - הפקולטה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: \n Details: \n \nאנו שמחים להזמינכם ל טקס השנתי של תוכנית המצוינות גבהים.\nבתוכ נית: \n\n\n דברי פתיחה: ד"ר יגאל גלוזמן\, מרכ ז תוכניות סילון וגבהים\n דבר דיקנית הפקו לטה\, פרופ' דניאלה רווה\n הרצאות סטודנטים מסיימי שנה שנייה/שלישית בתוכנית גבהים\n הצגת הסטודנטים החדשים\n טקס הענקת תעודות הצטיינות\n ארוחת צהרים\n\n CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1517@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251224T133000 DTEND;TZID=Asia/Jerusalem:20251224T143000 DTSTAMP:20251217T101059Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-12-24/ SUMMARY:Inlet Flow Distortions as a Source of Performance Degradation in Mi cro-Turbojet Engine Investigated through Experimental Quantification DESCRIPTION:Lecturer:Yakov Paltiel \n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering\n Institute:Technion – Israel Institute of Tech nology\n Location:Classroom 240\, 1st floor\, Aerospace Eng. building\n Zo om: https://technion.zoom.us/j/93549691766\n Abstract: Micro-Turbojet engi nes play a crucial role in various aerospace applications\, especially in small unmanned aerial vehicles (UAVs)\, target drones\, and experimental a ircraft. The overall performance of these engines is highly dependent on t he efficiency of their air intake systems. The geometry and configuration of the inlet and duct significantly influence pressure recovery\, airflow distortion\, and ultimately\, the engine's thrust and fuel efficiency. Amo ng the most critical components affected by these factors is the compresso r\, which is designed to operate under steady and uniform flow conditions. When subjected to distorted or non-uniform inlet flow\, the compressor ca n suffer from performance degradation\, and in severe cases\, encounter in stability phenomena such as rotating stall and surge.\n\nThese challenges highlight the importance of accurately quantifying the effects of inlet fl ow distortion on engine performance. However\, current predictive tools ar e often insufficient\, especially for Micro-Turbojet engines operating in complex or compact airframe environments. There is a clear need for a reli able and experimentally validated method to evaluate performance losses re sulting from various inlet conditions.\n\nThis seminar presents the develo pment of an experimental approach for a small-scale Micro-Turbojet engine to evaluate the effects of inlet distortions on engine performance. The re sults aim to support the optimization of air intake design and improve pre dictive capabilities for engine integration within specific airframes\, ul timately contributing to more efficient propulsion systems.\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 240\, 1st floor\, Aerospace Eng. building END:VEVENT BEGIN:VEVENT UID:0-1193@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251225T090000 DTEND;TZID=Asia/Jerusalem:20251225T150000 DTSTAMP:20251218T074723Z URL:https://aerospace.technion.ac.il/events/a-full-day-seminar-in-memory-o f-the-late-professor-emeritus-omri-rand/ SUMMARY:A commemorative symposium in memory of the late Professor Emeritus Omri Rand DESCRIPTION:Lecturer:A full-day seminar in memory of the late Professor Eme ritus Omri Rand\n Faculty:The Stephen B. Klein Faculty of Aerospace Engine ering\n Institute:Technion – Israel Institute of Technology\n Location:A uditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoom: ht tps://technion.zoom.us/j/93549691766\n Abstract: You are cordially invited to join us for a commemorative symposium in memory of the late Professor Emeritus Omri Rand. The event will be held in the faculty auditorium\, gat hering will be at 9:00 AM with light refreshments\, followed by a plenary session\, and a break for a light lunch.\n\n Check out the symposium progr am\n\n \;\n\n🔴Participation in this event is free\, but registratio n is compulsory.\n\n\nCLICK HERE TO REGISTER\n\n \;\n\n \;\n Detai ls: \n \n\n \; CATEGORIES:Seminars LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1194@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251225T090000 DTEND;TZID=Asia/Jerusalem:20251225T150000 DTSTAMP:20251218T074820Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%a2%d 7%99%d7%95%d7%9f-%d7%9e%d7%99%d7%95%d7%97%d7%93-%d7%9c%d7%96%d7%9b%d7%a8%d 7%95-%d7%a9%d7%9c-%d7%a4%d7%a8%d7%95%d7%a4-%d7%90%d7%9e%d7%a8%d7%99%d7%98% d7%95%d7%a1-%d7%a2/ SUMMARY:יום עיון מיוחד לזכרו של פרופ' אמריטוס עמרי רנד ז"ל DESCRIPTION:Lecturer:יום עיון מיוחד לזכרו של פרופ' אמריטוס עמרי רנד ז"ל\n Faculty:הפקולטה להנדסת אווירונוטיקה וחלל ע"ש סטיבן ב. קליין\n Insti tute:הטכניון - מכון טכנולוגי לישראל\n Location:א ודיטוריום 235 - הפקולטה להנדסת אוירונוטיק ה וחלל\n Zoom: \n Abstract: \nיום עיון מיוחד לזכרו של פרופ' אמריטוס עמרי רנד ז"ל.\nיום העיון י תקיים באודיטוריום הפקולטה\, התכנסות וכיב וד קל בשעה 9:00\, בשעה 9:30 יחל מושב המליאה. לק ראת 12:00 תתקיים הפסקה לארוחת צהרים קלה\, וה משך המליאה.\n \;\n\nלחץ כאן לתוכנית היום\n D etails: \n CATEGORIES:סמינרים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1518@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251229T133000 DTEND;TZID=Asia/Jerusalem:20251229T143000 DTSTAMP:20251211T103102Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-12-29/ SUMMARY:Colloquium Series: Towards Scalable Online Planning Under Uncertain ty in Partially Observable Environments DESCRIPTION:Lecturer:Vadim Indelman\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering and the Faculty of Data and Decision Sciences (Se condary Appointment)\n Institute:Technion – Israel Institute of Technolo gy\n Location: Auditorium 235\, The Faculty of Aerospace Engineering\, Tec hnion\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: Decision- making under uncertainty in partially observable environments is a central challenge in AI and robotics. \n\nIt is fundamental to the operation of a utonomous systems that must act reliably and safely despite incomplete\, i mperfect\, or ambiguous information. This talk will present recent advance s in scalable online planning in such settings\, where the problem is comm only formulated as a Partially Observable Markov Decision Process (POMDP) or addressed through belief space planning. These include POMDP planning w ith hybrid belief representations\, which capture real-world complexities such as viewpoint-dependent semantic observations and ambiguous data assoc iations\, as well as methods for leveraging past experience to accelerate online POMDP planning in continuous spaces significantly. \n\nThe second p art of the talk will focus on a recently developed framework for simplifyi ng decision-making under uncertainty problems with formal performance guar antees. This framework will be presented from multiple perspectives\, show ing how it enables fast and adaptive online POMDP planning. Finally\, its extension to multi-agent systems will be presented\, highlighting how it s upports provably consistent decision-making even when agents maintain inco nsistent beliefs due to limited data-sharing.\n\n \;\n\n \;\n Deta ils: \n CATEGORIES:Seminars,סמינרים LOCATION: Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1519@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251231T013000 DTEND;TZID=Asia/Jerusalem:20251231T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-12-31/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1627@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251231T123000 DTEND;TZID=Asia/Jerusalem:20251231T143000 DTSTAMP:20251216T154607Z URL:https://aerospace.technion.ac.il/events/the-kfir-the-first-israeli-fig hter-jet/ SUMMARY:The KFIR - The First Israeli Fighter Jet DESCRIPTION:Lecturer:Colonel (Res.) Ben-Ami Gov headed the first Israeli fi ghter jet project\n Faculty:\n Institute:\n Location:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: The story of the pioneering and rare project\, which combined the best of Israeli i mprovisation\, along with the talent\, entrepreneurship\, and intelligence of everyone involved.\nLecturer: Colonel (Res.) Ben-Ami Gov headed the fi rst Israeli fighter jet project.\n\n\nOrganized together with the Israel Society of Aeronautics &\; Astronautics\n Details: \n ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2025/12/KFIR-2-WWW.jpg CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1628@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20251231T123000 DTEND;TZID=Asia/Jerusalem:20251231T143000 DTSTAMP:20251216T160002Z URL:https://aerospace.technion.ac.il/he/events/%d7%9b%d7%a4%d7%99%d7%a8-%d 7%a1%d7%99%d7%a4%d7%95%d7%a8%d7%95-%d7%a9%d7%9c-%d7%9e%d7%98%d7%95%d7%a1-% d7%94%d7%a7%d7%a8%d7%91-%d7%94%d7%99%d7%a9%d7%a8%d7%90%d7%9c%d7%99-%d7%94% d7%a8%d7%90%d7%a9%d7%95/ SUMMARY:כפיר - סיפורו של מטוס הקרב הישראלי הר אשון DESCRIPTION:Lecturer:אל״מ (מיל.) בן עמי גוב\n Faculty:\n Ins titute:\n Location:אודיטוריום 235 - הפקולטה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: \nאירוע במס גרת האגודה למדעי התעופה והחלל בישראל:\n ב שנות ה־60 של המאה הקודמת\, בעידן שבו עדיין לא היתה בישראל תשתית הנדסית וטכנולוגית ש ל ממש\, החליט משרד הביטחון לפתח ולייצר מט וס קרב תוצרת כחול־לבן המשימה הוטלה על בן  עמי גוב\, ראש ענף בחיל האוויר\, מהנדס מכו נות בהשכלתו וקצין טכני בהכשרתו. גוב מונה לראש הפרויקט\, שהתנהל במשך שנים בסודיות מ וחלטת ונשא את שם הקוד "רעם". בשיתוף פעולה עם התעשייה האווירית קרם הפרויקט עור וגיד ים כשהוא יוצר יש מאין תעשייה טכנולוגית מ קומית\, שעד היום קוצרת מדינת ישראל את פיר ותיה.\nראשון המריא מטוס הנשר\, שאף השתתף - ובהצלחה מרובה - במלחמת יום הכיפורים\, ובע קבותיו נסק הכפיר\, שהתעלה על קודמו. שני מט וסי הקרב הצטיינו בביצועים אוויריים והפג ינו יכולות מתקדמות. תקופה מסוימת\, עד שהח ל בחיל האוויר עידן מטוסי הקרב האמריקאיים \, נחשבו הכפיר והנשר למטוסי קו ראשון בספר ו מהרעם נסק הכפיר מגולל בן עמי גוב את סיפ ורו של הפרויקט החלוצי והנדיר\, ששילב את י כולת האלתור הישראלית במיטבה\, יחד עם הכיש רון\, היזמות והתבונה של כל מי שהיו מעורבי ם בו.\nאל״מ (בדימוס) בן עמי גוב עמד בראש פר ויקט מטוס הקרב הישראלי הראשון\, שממנו המר יאו בהצלחה מטוסי הנשר והכפיר. גוב\, יליד י רושלים\, השתתף במלחמת העצמאות במבצע נחשו ן ובמבצע מכבי\, היה ממקימי קיבוץ סער\, ומר אשוני טכנאי המטוסים בחיל האוויר. במקביל לתפקידיו כקצין טכני בחיל האוויר\, סיים לי מודי הנדסת מכונות וייצור בטכניון. לאחר ש חרורו מחיל האוויר כיהן בשורה ארוכה של תפ קידים\, ביניהם נציג חברת "טלדיין" בישראל\, מנכ״ל משרד התקשורת\, יו״ר מנועי בית שמש\, חבר בנשיאות התאחדות התעשיינים ועוד. על ת פקידו כראש פרויקט מטוס הקרב זכה גוב בפרס ביטחון ישראל.\n \;\n\n\n\n\n Details: \n ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2025/12/KFIR-2-WWW.jpg CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1521@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260107T013000 DTEND;TZID=Asia/Jerusalem:20260107T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-01-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1625@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260107T123000 DTEND;TZID=Asia/Jerusalem:20260107T143000 DTSTAMP:20251201T150545Z URL:https://aerospace.technion.ac.il/events/the-annual-silon-event/ SUMMARY:The Annual SILON Event DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:Auditorium 235\, T he Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abstract: We are planning a special annual event for the SILON Program in which faculty me mbers and students will participate.\n\nThis is a great opportunity for yo u to get to know each other\, to get updated on the program's procedures\, and to get to know the faculty members and the research they are performi ng. The prime goal is to assist our SILON students in finding an advisor f or their research project. In addition\, it is an opportunity for non-SILO N students to get familiar with the research in the faculty and to conside r graduate studies.\n\nThe event will take place on Wednesday\, January 7\ , 2025 (12:30-2:30 PM) in the Faculty Auditorium (Room 235)\n\nSchedule:\n \n12:30 PM\nOpening remarks and information for students in the program:\n \n Dr. Yigael Gluzman - Coordinator of the SILON and Heights Excellence P rograms\n Yehudit Greenberg - Graduate Studies Coordinator\n\n1:00 PM-2:0 0 PM\nExposure to research at the faculty: Lectures by faculty members on selected topics (approximately 12 lectures of approximately 5 minutes each )\n\n2:00 PM-2:30 PM\nPizza 🍕 \, beer 🍻 and free discussion\n Detail s: \n ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2017/02/SILON.jpg CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1626@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260107T123000 DTEND;TZID=Asia/Jerusalem:20260107T143000 DTSTAMP:20251202T084852Z URL:https://aerospace.technion.ac.il/he/events/%d7%9b%d7%a0%d7%a1-%d7%a1%d 7%99%d7%9c%d7%95%d7%9f-%d7%94%d7%a9%d7%a0%d7%aa%d7%99/ SUMMARY:כנס סילון השנתי DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:אודיטוריו ם 235 - הפקולטה להנדסת אוירונוטיקה וחלל\n Zo om: \n Abstract: הנכם מוזמנים לאירוע סילון השנת י\, אירו ע המפגיש בין חברי סגל והסטודנטים בפקולטה.\n\nזו הזדמנות מצויינת להכיר אחד א ת השני\, להתעדכן בנהלי התכנית\, ולהכיר את חברי הסגל בפקולטה ואת המחקרים שהם עושים\, כל אחד בתחומו. אחת ממטרות המפגש היא לסיי ע לסטודנטים הלומדים במסגרת תכנית סילון ל מצא מנחה לפרויקט מחקר. בנוסף\, זו הזדמנות לכלל הסטודנטים בפקולטה להחשף למחקרים ומ גוון התחומים והאפשרויות להשתלב בלימודים לתארים מתקדמים.\n\nלוח זמנים:\n\n12:30\nדברי פ תיחה ומידע לסטודנטים בתכנית:\n\n ד"ר יגאל גלוזמן - מרכז תכניות המצוינים סילון וגבה ים\n יהודית גרינברג - רכזת תארים מתקדמים\n \n13:00-14:00\nחשיפה למחקר בפקולטה: הרצאות חברי סגל הפקולטה על מחקריהם המגוונים. כ 12 הרצ אות קצרות של כ 5 דקות כל אחת.\n\n14:00\nפיצות 🍕 בירות 🍻 ודיון חופשי\n\n \;\n Details: \n ATTACH;FMTTYPE=image/jpeg:https://aerospace.technion.ac.il/wp-content/uplo ads/2017/02/SILON.jpg CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1522@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260112T133000 DTEND;TZID=Asia/Jerusalem:20260112T143000 DTSTAMP:20251222T133330Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-01-12/ SUMMARY:Efficient high-fidelity turbulence modeling using convolutional neu ral networks DESCRIPTION:Lecturer:Amir Israel\n Faculty:Aerodynamics\n Institute:Technio n – Israel Institute of Technology\n Location:Classroom 165\, ground flo or\, Library\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/935496917 66\n Abstract: \n\n\nIn the past few years\, the field of Machine Learning (ML) in general\, and Deep Learning (DL) in particular\, has been getting a lot of attention\, both due to the continued growth of computational po wer\, and the generation of large datasets. The field of fluid mechanics i s rich in large amount of datasets from experiments and simulations.  Mor eover\, the fact that fluid flow often contains reoccurring patterns that can be studied and predicted makes fluid mechanics an excellent candidate for the use of ML.\nThis talk discusses the ability of convolutional neura l networks (CNN) to replace classic turbulence models for a specific set o f problems efficiently. Although some attempts have been made to use neura l networks to create a data-informed turbulence model\, none have managed to do so efficiently for an unsteady case with walls. The unique approach of this work\, necessitating fast predictions\, required using a specific CNN architecture and the use of image processing algorithms. The model can be effectively used for problems that require a lot of high-fidelity simu lations of flow fields that share similarities. Nevertheless\, the chosen CNN would not necessarily improve cases substantially different from the o nes used for the model dataset.\nThe focus is on predicting the Reynolds s tresses using CNNs. Specifically\, U-Net . The chosen test case is a flow over a cylinder since it presents different patterns in a relatively low-R eynolds number range and has a lot of documentation for comparison. While most papers attempt to create a general model\, this paper explores the po ssibility of a case-specific DL model\, enabling the use of different meth ods from the ones used so far. Nevertheless\, some generalization is still required from the model and will be tested. Specifically\, its ability to generalize over various Reynolds numbers. \;\n\n \;\n\n\n\n Detai ls: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1523@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260114T133000 DTEND;TZID=Asia/Jerusalem:20260114T143000 DTSTAMP:20251222T133249Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-01-14/ SUMMARY:Morphology-Controlled Sheet Spray Cooling from Convergent Micronozz les for Hypersonic Leading Edges DESCRIPTION:Lecturer:Alexandros Peteinaris\n Faculty:The Stephen B. Klein F aculty of Aerospace Engineering at the Technion \n Institute:Technion – Israel Institute of Technology\n Location:Classroom 165\, ground floor\, L ibrary\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n A bstract: Thermal management for hypersonic leading edges must remove extre me heat fluxes within ultra-thin\, aerodynamically constrained structures\ , where passive approaches are limited by available volume and surface-tem perature margins. This study experimentally investigates convergent micro- nozzle sheet sprays as an active cooling concept for leading-edge integrat ion. The goal is to combine minimal coolant thickness and consumption with strong near-wall renewal and mixing.\nLiquid sheets are generated using l ithographically fabricated micronozzles and characterized via high-speed s hadowgraph imaging to quantify breakup and atomization pathways. The measu rements show that increasing the flow rate and outlet confinement expand t he sheet size and extend the stable-sheet region. In contrast\, the conver gent angle systematically reshapes the sheet by redistributing momentum at the nozzle exit. A scaling analysis predicts stable-sheet dimensions and is used to construct a Weber-number-convergent angle-regime map that class ifies the observed sheet morphologies.\nDownstream atomization is quantifi ed using laser diffraction\, which reveals single-peak and bimodal droplet -size distributions associated with specific regimes and highlights the st rong influence of the outlet aspect ratio on mean droplet diameters. Stead y-state infrared thermography provides spatially resolved heat-transfer co efficient maps\, directly linking spray structure to cooling performance. For the conditions tested\, more coherent\, planar sprays provide higher a rea-averaged cooling than fully atomized sheets. However\, targeted regime selection and local morphological manipulation can enhance peak heat tran sfer at the leading edge\, where it is most needed. These results provide experimentally grounded design rules for micro-nozzle geometry and flow ra te to tailor cooling footprints for hypersonic thermal protection.\n\n&nbs p\;\n\n \;\n\n \;\n\n \;\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1524@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260119T013000 DTEND;TZID=Asia/Jerusalem:20260119T023000 DTSTAMP:20251118T063841Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-01-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1632@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260121T123000 DTEND;TZID=Asia/Jerusalem:20260121T143000 DTSTAMP:20260111T164914Z URL:https://aerospace.technion.ac.il/events/the-lavi-its-contribution-and- its-in-return/ SUMMARY:The Lavi – Its Contribution and Its In Return DESCRIPTION:Lecturer:Menahem Shmul\n Faculty:\n Institute:\n Location:Audit orium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoom: \n Abs tract: \n\nYou are invited to another lecture as part of the activities of the Israel Society of Aeronautics and Astronautics\n\nThe story of the Is rael Aerospace Industries (IAI) from its establishment as “Bedek Metosim ” to the proof of the Israeli ability to initiate\, plan\, develop\, and fly the Lavi\, a fighter aircraft considered to be the best of its genera tion.\n\n \;\n\nLecturer: Menahem Shmul\, fourth-generation in Israel\ , a fighter pilot in the IAF\, who fought in 4 wars\, and worked as a test pilot\, and later as chief\, and director of air operations\, at the IAI. Menahem flew the Lavi on its first flights and on most of the approximate ly 240 flights performed by the 3 Lavi prototypes.\n\nHe served for about 10 years as Executive V.P - General Manager of the Military Aircraft Group . He continued to work at the company in other positions until his retirem ent\, about six months ago at the age of 80\, after 55 years of working at the company.\n\n \;\n\n \;\n\nPlease note: the lecture will be in Hebrew\n Details: \n CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1633@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260121T123000 DTEND;TZID=Asia/Jerusalem:20260121T143000 DTSTAMP:20260111T165350Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%9c%d7%91%d7%99%d7 %90-%d7%aa%d7%a8%d7%95%d7%9e%d7%aa%d7%95-%d7%95%d7%aa%d7%9e%d7%95%d7%a8%d7 %aa%d7%95/ SUMMARY:הלביא – תרומתו ותמורתו DESCRIPTION:Lecturer:מנחם שמול\n Faculty:\n Institute:\n Location: אודיטוריום 235 - הפקולטה להנדסת אוירונוטי קה וחלל\n Zoom: \n Abstract: \n\nאתם מוזמנים להרצאה נוספת במסגרת פעילות האגודה למדעי התעופה והחלל בישראל:\n\n סיפורה של התעשייה האווי רית. מהקמתה כמכון בדק מטוסים ועד הוכחת הי כולת הישראלית ליזום\, לתכנן\, לפתח ולהטיס את הלביא\, מטוס קרב שנחשב לטוב ביותר בדור ו.\n\nהמרצה:  מנחם שמול\, דור רביעי בארץ\, טי יס קרב שלחם  ב - 4 מלחמות\, ועבד כטייס ניסו י\, ובהמשך ראשי\, ומנהל מבצעי אוויר\, בתעשי יה האווירית. מנחם הטיס את הלביא בטיסותיו הראשונות\, ובחלק הארי מתוך כ-240 טיסות שביצ עו 3 אבי הטיפוס.\n\nכיהן כ – 10 שנים בתפקיד ס מנכ"ל\, מנהל חטיבת כלי טיס צבאיים.\n\nהמשיך לעבוד בחברה בתפקידים נוספים\, עד לפרישתו\ , לפני כחצי שנה\, בגיל 80\, אחרי 55 שנות עבודה בה.\n\n\n Details: \n CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1641@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260125T123000 DTEND;TZID=Asia/Jerusalem:20260125T143000 DTSTAMP:20260121T140040Z URL:https://aerospace.technion.ac.il/events/space-campus-il/ SUMMARY:Space Campus IL DESCRIPTION:Lecturer:\n Faculty:The Stephen B. Klein Faculty of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoo m: \n Abstract: We’re kicking off the Israeli Space week with a massive event featuring guests you don't see everyday:\n\n👨‍🚀 Astronaut Ra ndy Bresnik will be joining us for a rare visit! ⚖️ Alongside NASA’s Legal Advisor for International &\; Space Law who will deliver a fasci nating lecture on the future of humanity beyond Earth.\n\nIf space is in y our DNA—this is the event for you!\n\n📍 Where: Aerospace Engineering Auditorium\, Technion\n📅 When: Sunday\, January 25th at 12:30 PM\n\n 🔗 Register now: https://forms.monday.com/forms/0999330f6c07b1f09434cc8b 95063dea?r=euc1\n\n🔥 We recommend wearing our community T-shirts to all Space Week events. See you there! 🚀\n Details: \n An inspiring lecture by astronaut Randy Breznik and legal advisor for international and space law Revka Breznik (NASA) CATEGORIES:Events LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1642@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260125T123000 DTEND;TZID=Asia/Jerusalem:20260125T143000 DTSTAMP:20260121T140706Z URL:https://aerospace.technion.ac.il/he/events/%d7%90%d7%99%d7%a8%d7%95%d7 %a2-%d7%a7%d7%94%d7%99%d7%9c%d7%aa-space-il-campus/ SUMMARY:אירוע קהילת Space IL Campus DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אווירונ וטיקה וחלל ע"ש סטיבן ב. קליין\n Institute:הטכני ון - מכון טכנולוגי לישראל\n Location:אודיטורי ום 235 - הפקולטה להנדסת אוירונוטיקה וחלל\n Zoom: \n Abstract: אנחנו פותחים את השבוע באירוע ח גיגי עם אורחים שלא פוגשים כל יום: 👨‍🚀 ה אסטרונאוט רנדי ברזניק (Randy Bresnik) מגיע לביק ור נדיר! ⚖️ ולצידו\, היועצת המשפטית של נא ס"א לענייני משפט בינלאומי ודיני חלל\, בהר צאה מרתקת על העתיד של האנושות מחוץ לכדור הארץ.\n\nלכל מי שהחלל זורם לו בוורידים – ז ה אירוע שאסור לפספס!\n\n📍 איפה? אודיטוריו ם הפקולטה לאווירונאוטיקה וחלל\, הטכניון. 📅 מתי? יום ראשון\, 25.01 בשעה 12:30.\n\n🔗 ההרשמ ה מראש: https://forms.monday.com/forms/0999330f6c07b1f09434cc8b95063d ea?r=euc1\n\n\n Details: \n שבוע החלל הישראלי 2026 יוצא לדרך בטכניון - ובגדול! 🛰️✨ CATEGORIES:אירועים LOCATION:אודיטוריום 235 - הפקולטה להנדסת אוירו נוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1630@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260126T133000 DTEND;TZID=Asia/Jerusalem:20260126T143000 DTSTAMP:20251231T105927Z URL:https://aerospace.technion.ac.il/events/experimental-characterization- and-modeling-of-cavitation-in-radial-flow-between-two-overlying-plates-wit h-varying-gaps/ SUMMARY:Experimental characterization and modeling of cavitation in radial flow between two overlying plates with varying gaps DESCRIPTION:Lecturer:Samruddhi Salunke\n Faculty:The Stephen B. Klein Facul ty of Aerospace Engineering\n Institute:Technion – Israel Institute of T echnology\n Location:Classroom 165\, ground floor\, Library\, Aerospace En g.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: In the prese nt study\, we focus on characterizing and modelling cavitation physics in radial flow within a thin layer between two stationary plates. This geomet ry is relevant to aviation fuel pumps\, where cavitation often leads to pr emature and unexpected material degradation and failure.  In this geometr y\, the pressurized liquid flowing through a cylindrical feed nozzle is fo rced to turn ninety degrees and then move radially between two flat plates . The transition from axial to purely radial flow near the orifice results in extreme radial dilatation. If nuclei are present\, this will lead to t heir rupture and the formation of cavitation bubbles. These bubbles form a cavitating cloud in the form of a disk surrounding the central inlet feed port\, with a distinct boundary between the bubble cloud and liquid obser ved at the radial location of bubble collapse.\n\nIn our experimental effo rt\, we quantified and compared cavitating disk behaviour for distilled wa ter and dodecane (used as a surrogate for aviation fuel) across various ga ps between the plates\, ranging from 0.025 mm to 0.5 mm\, and inlet-outlet pressure ratios in the range 4--11. By employing high-speed imaging along side high-frequency  and radial pressure measurements\, we captured both the time-averaged and unsteady features of the disk-shaped cavitation clou d\, specifically investigating the location of its abrupt radial collapse and the oscillatory behaviour of the cavity disk perimeter.  In the semin ar\, a detailed discussion on the differences in radial cavitation behavio ur between distilled water and dodecane will be presented.\n\nIn our model ling efforts\, the spatial Rayleigh-Plesset equation was utilized to predi ct the abrupt radial collapse distance of the cavitation disk as a functio n of gap thickness between the plates. Additionally\, we proposed a barotr opic model for radial mean pressure profile prediction\; this model showed good agreement when validated against experimental measurements across di fferent gaps and inlet-outlet pressure ratios.\n\n \;\n\n \;\n\n& nbsp\;\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1631@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260128T133000 DTEND;TZID=Asia/Jerusalem:20260128T143000 DTSTAMP:20260115T132031Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-01-14-2/ SUMMARY:Colloquium: Novel Chemical Propulsion Research DESCRIPTION:Lecturer:Professor Emeritus Alon Gany\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering\n Institute:Technion – Israel Ins titute of Technology\n Location:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion\n Zoom: https://technion.zoom.us/j/93549691766\n Ab stract: The lecture will present some novel and innovative propulsion conc epts and investigations conducted in our research group. The subject of al uminized solid propellant combustion will be presented\, highlighting the problem of particle agglomeration and slag formation and ways to reduce th is phenomenon. Solid fuel ramjets (SFRJ) and scramjets will be discussed a s well\, including the concept of self-propelled gun-launched projectiles. A novel concept of enhancing the fuel burning rate and thrust by expandab le graphite additives will be demonstrated. Extension of the ramjet concep t to high-speed water-breathing underwater ram rocket vehicles will reveal a powerful propulsion means\, particularly when adding water-reactive met al particles to the fuel grain. The presentation of those subjects and oth ers will include video clips and new data.\n\n \;\n\nAlon Gany is Prof essor Emeritus at the Faculty of Aerospace Engineering of the Technion. He joined the faculty in 1979 and was the holder of the Fohrman Chair in Aer onautical Engineering. Alon was the academic advisor for the planning and construction of the Fine Rocket Propulsion Center and headed it for 18 yea rs. During the years 2000-2002 he was also the Dean of Students of the Tec hnion. Prof. Gany received all his academic degrees from the Technion. He was a postdoc and later-on a visiting professor at Princeton University an d spent another sabbatical year at the Naval Postgraduate School\, Montere y\, CA as a Senior NRC Research Fellow.\nAlon’s research and interest ar e in aerospace propulsion (rockets\, ramjets)\, marine innovative propulsi on\, combustion\, and hydrogen energy.  He is a Member of the US National Academy of Engineering (NAE)\, the International Academy of Astronautics (IAA) and was recently elected to the Israel National Academy of Sciences and Humanities. Alon is Fellow and Honorary Fellow in 4 international asso ciations including AIAA. Among his main honors are the 2025 AIAA Wyld Prop ulsion Award\, Mafat’s Lifetime Award for Innovative Mind\, recognition as Technion’s Permanent Distinguished Lecturer\, and a conference Advanc es in Chemical Propulsion honoring him at his 75th Birthday.\nAlon advised over 100 students toward master’s and doctoral degrees. He published wi th his students and colleagues over 150 journal papers\, 450 conference pr esentations\, a course textbook on propulsion (in Hebrew)\, and some 20 pa tents worldwide.\nAlon is married to Ruti\, and they have 3 children and 9 grandchildren.\n\n \;\n\n \;\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion END:VEVENT BEGIN:VEVENT UID:0-1528@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260202T013000 DTEND;TZID=Asia/Jerusalem:20260202T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-02-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1529@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260204T013000 DTEND;TZID=Asia/Jerusalem:20260204T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-02-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1530@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260209T133000 DTEND;TZID=Asia/Jerusalem:20260209T143000 DTSTAMP:20260104T144955Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-02-09/ SUMMARY:Physically Consistent Outflow Boundary Conditions for Global Stabil ity Analysis of Bluff Body Wakes DESCRIPTION:Lecturer:Amit Sigawi\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering\n Institute:Technion – Israel Institute of Technol ogy\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Z oom: https://technion.zoom.us/j/93549691766\n Abstract: Global linear stab ility analysis of bluff body wakes must be carried out on truncated comput ational domains\, even though the physical problem is unbounded. Because t he global eigenfunctions are not known a priori\, the outlet location and the outflow boundary condition are often selected heuristically and valida ted a posteriori by inspecting the computed eigenspectrum and eigenfunctio ns. In practice\, standard outflow treatments can create a localized non-p hysical region near the outlet\, which is then identified in post-processi ng and excluded from physical interpretation. To mitigate these outlet eff ects\, the downstream boundary is often moved farther away by extending th e computational domain\, increasing the computational cost.\n\n \;\n\n  \;\n\nThis seminar presents a matrix-forming BiGlobal stability frame work based on finite-difference discretization and assesses how the outflo w boundary condition influences the predicted eigenspectrum and eigenmodes . Common outlet closures (Dirichlet\, Neumann\, and extrapolation-type) ar e compared with a physically consistent Robin boundary condition that inco rporates local linear stability theory information at the outlet. For stea dy\, incompressible\, low Reynolds number (of order of 100) wakes of cylin ders and airfoils at high angles of attack\, the proposed Robin condition eliminates outlet-induced artifacts and yields robust convergence\, even w hen the computational domain is severely truncated. Our findings pave the way for efficient and accurate computations of global eigenfunctions in mo re complex flows.\n\n \;\n\n \;\n\n \;\n\n \;\n Details: \ n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1531@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260211T133000 DTEND;TZID=Asia/Jerusalem:20260211T143000 DTSTAMP:20260101T075914Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-02-11/ SUMMARY:Integrated Target Allocation and Guidance Strategy using Virtual Ta rgets DESCRIPTION:Lecturer:Kirill Reznik\n Faculty:The Stephen B. Klein Faculty o f Aerospace Engineering\n Institute:Technion – Israel Institute of Techn ology\n Location:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract: \n\n\nThe resear ch investigates a Shoot-Shoot-Look engagement\, in which two waves of mult iple pursuers are deployed to intercept multiple targets. The first wave i s assigned to targets at the beginning of the scenario. The second wave co nsists of backup pursuers\, whose assignments to the actual targets are de layed until the outcomes of the first-wave intercepts become known. Before their final assignments\, the backup pursuers move toward virtual targets to allow several subsequent reallocation options. The allocation aims to minimize the final expected number of surviving targets. Each interception attempt is probabilistic and depends on the time of flight and heading ch ange required to reach the target. Discrete allocations\, together with th e continuous evolution of pursuer and target kinematic states under simple motion models\, are naturally modeled as a stochastic Markov Decision Pro cess. A general multi-stage formulation with repeated virtual target reall ocations can be solved optimally using Dynamic Programming\, but the assoc iated curse of dimensionality leads to a rapidly increasing computational cost. To mitigate this complexity\, the problem is reduced to a single dec ision stage\, assuming that first-wave intercepts occur within a narrow ti me window. The proposed reduction yields an equivalent finite-dimensional nonlinear optimization problem with respect to the initial headings of the backup pursuers. In addition\, a simplified sequential Greedy allocation algorithm is developed. Monte Carlo simulations show that it closely appro ximates the optimal solution for scenarios in which the first-wave pursuer s have similar intercept probabilities\, whereas\, for highly heterogeneou s first-wave outcomes\, Dynamic Programming yields significantly superior results.\n\n \;\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1532@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260216T013000 DTEND;TZID=Asia/Jerusalem:20260216T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-02-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1533@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260218T013000 DTEND;TZID=Asia/Jerusalem:20260218T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-02-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1534@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260223T013000 DTEND;TZID=Asia/Jerusalem:20260223T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-02-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1535@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260225T013000 DTEND;TZID=Asia/Jerusalem:20260225T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-02-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1536@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260302T013000 DTEND;TZID=Asia/Jerusalem:20260302T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-03-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1537@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260304T013000 DTEND;TZID=Asia/Jerusalem:20260304T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-03-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1538@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260309T013000 DTEND;TZID=Asia/Jerusalem:20260309T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-03-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1539@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260311T133000 DTEND;TZID=Asia/Jerusalem:20260311T143000 DTSTAMP:20260308T125523Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-03-11/ SUMMARY:Spatially resolved heat transfer coefficients in water-sheet spray cooling at sub-saturation wall temperatures using infrared thermography DESCRIPTION:Lecturer:Charles Touitou\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering at the Technion \n Institute:Technion – Israel Institute of Technology\n Location:The seminar will be held online only v ia Zoom\n Zoom: https://technion.zoom.us/j/94050711666\n Abstract: \n\n\nS pray cooling is a high-performance thermal-management approach used when c onventional single-phase convection becomes limited by available area or m ass flow. However\, obtaining spatially resolved measurements of local hea t transfer coefficients remains challenging.\nThis work presents an experi mental method for quantifying spatially resolved local heat transfer coeff icients during water-sheet spray cooling at sub-saturation wall temperatur es. The approach combines uniform Joule heating of a 25 μm thick metallic foil with infrared thermography in a multilayer glass-adhesive-foil assem bly. A conduction-based reconstruction procedure accounting for through-th ickness thermal resistance\, lateral heat spreading\, backside convection\ , and radiation losses is used to determine the wetted-surface temperature and local convective heat flux\, enabling direct mapping of the heat tran sfer coefficient over the full spray footprint.\nThe measurement technique is first validated using a fully developed single round air jet over a wi de range of Reynolds numbers from 9\,000 to 60\,000\, and multiple imposed heat flux levels (0.76 – 2.5 kW/cm2). Measurements obtained with Consta ntan and Inconel 600 heater foils yield nearly identical Nusselt number di stributions and axisymmetric stagnation-region peaks\, demonstrating insen sitivity to heater material and heat-flux level.\nThe validated method is then applied to cooling produced by a convergent microfluidic nozzle gener ating a planar water sheet that atomizes prior to impact. The measurements are still independent on the heat flux level (7 – 54 kW/cm2) and reveal strongly non-uniform heat transfer footprints governed by water sheet spr eading and breakup dynamics. By restricting operation to sub-saturation wa ll temperatures\, the experiments isolate single-phase convective transpor t and provide benchmark datasets for spray-cooling models in the absence o f boiling.\nThe proposed technique provides a robust framework for high-re solution characterization of spray cooling performance and is broadly appl icable to thermal management systems and microfluidic cooling architecture s.Charles Touitou has been an MSc student in the Faculty of Aerospace Engi neering since 2024 and currently works as an aerodynamics engineer at Elbi t Systems.\n\nSpecial Notice: Following a situational assessment held by t he Technion Management\, and in accordance with Home Front Command guideli nes\, the following Aerospace Engineering seminar will be held online only via Zoom.\n\n \;\n\n \;\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:The seminar will be held online only via Zoom END:VEVENT BEGIN:VEVENT UID:0-1643@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260318T133000 DTEND;TZID=Asia/Jerusalem:20260318T143000 DTSTAMP:20260318T081838Z URL:https://aerospace.technion.ac.il/events/optimal-estimation-aware-motio n-a-control-centric-optimization-framework/ SUMMARY:Optimal Estimation-Aware Motion: A Control-Centric Optimization Fra mework DESCRIPTION:Lecturer:Liraz Mudrik\n Faculty:Mechanical and Aerospace Engine ering Department\n Institute:Naval Postgraduate School\n Location:\n Zoom: https://technion.zoom.us/j/94050711666\n Abstract: This talk focuses on t he intersection of trajectory generation with estimation theory\, specific ally addressing the challenges of operating in uncertain or adversarial en vironments\, such as GPS-denied scenarios. In such scenarios\, trajectorie s must be aware of the estimation process and actively maximize informatio n gain. However\, coupling estimation metrics with high-fidelity nonlinear dynamics creates complex\, nonconvex optimal control problems that challe nge standard computational techniques\, such as the popular pseudospectral methods. Generating sensor-based trajectories naturally requires uniform time spacing\, which introduces well-known limitations such as the Runge p henomenon and the impossibility theorem. This talk outlines a unified rese arch architecture that bridges the gap between high-level mission goals an d efficient computational methods with theoretical guarantees.\n\nFirst\, to enable efficient planning in complex domains\, we introduce the mixed B ernstein-Fourier approximants. This representation is specifically designe d to encode the complex periodic behaviors inherent to missions such as ob server trajectory design and mine countermeasures\, significantly reducing the dimensionality of the search space without sacrificing accuracy.\n\nS econd\, we present a control-centric optimization framework that fundament ally reinterprets optimization algorithms as continuous-time dynamical sys tems. This approach provides a general theory for synthesizing solvers wit h tunable convergence profiles\, ranging from asymptotic to fixed and pres cribed-time. By leveraging results from Lyapunov stability theory\, this f ramework allows embedding constraints\, ensuring strictly feasible traject ories. This establishes a theoretical foundation for scalable autonomy\, d emonstrated through constrained optimization\, minimax problems\, and gene ralized Nash equilibrium seeking. These results pave the way for future re search in robust\, scalable aerospace autonomy where real-time performance and safety guarantees are paramount.\n\nDr. Liraz Mudrik is currently a P ostdoctoral Fellow in the Department of Mechanical and Aerospace Engineeri ng at the Naval Postgraduate School. He received his Ph.D. in Aerospace En gineering (direct track) from the Technion–Israel Institute of Technolog y in 2023\, where he also earned his B.Sc. (cum laude).\n\n \;\n\nPlea se be advised that all seminars scheduled for the near future\, and until further notice\, will be held online only via Zoom. This transition allows us to maintain our academic calendar and ensure the safety and participat ion of our community regardless of location. We are committed to ensuring these virtual sessions are delivered promptly and effectively. We apprecia te your continued flexibility and look forward to seeing you in our virtua l seminars.\n\n \;\n Details: \n CATEGORIES:Seminars,סמינרים END:VEVENT BEGIN:VEVENT UID:0-1542@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260323T013000 DTEND;TZID=Asia/Jerusalem:20260323T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-03-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1647@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260330T133000 DTEND;TZID=Asia/Jerusalem:20260330T143000 DTSTAMP:20260324T092329Z URL:https://aerospace.technion.ac.il/events/dynamic-identification-and-con trol-of-ultralight-deployable-space-structures/ SUMMARY:Dynamic Identification and control of Ultralight Deployable Space S tructures DESCRIPTION:Lecturer:Eyal Baruch\n Faculty:Lynn Booth and Kent Kresa Depart ment of Aerospace\n Institute:California Institute of Technology\n Locatio n:\n Zoom: https://technion.zoom.us/j/94130704561 \n Abstract: As space mi ssions such as solar sails\, reflector antennas and solar arrays increase in size\, their dynamics become ever more important\, since large deflecti ons can lead to efficiency loss\, damage\, or stability loss. The first st ep in addressing these problems is the accurate identification of system d ynamics\, most notably vibration mode shapes\, natural frequencies\, and d amping ratios. However\, these systems often cannot be tested at full scal e prior to deployment\, and numerical simulations may overlook key compone nts\, such as the correct damping mechanisms. This problem is further inte nsified by the complexity of carbon fiber thin shells\, which serve as the fundamental building blocks of ultralight deployable structures. For such systems\, classical similitude methods such as dimensional analysis (DA) are inapplicable\, since parameters such as shell thickness and the stiffn ess matrix cannot be experimentally scaled.\n\nTo address these challenges \, I propose a data driven similitude method that exploits multiple scaled experiments to overcome the issue of distortion in partial similitude. In addition\, to account for the inherent uncertainty in ultralight thin-she ll structures\, this method is extended into a Bayesian-inference-based st atistical similitude model\, which allows for uncertainty quantification i n the acquired scaling law. The model is constructed from simulated data a nd updated based on experimental measurements\, enabling statistical model updating of the scaling model. Finally\, I present a stiff switching damp ing mechanism that leverages the tensioning typical of deployable space st ructures to actively suppress vibrations.\n\nBio:\n\nDr. Eyal Baruch is a Postdoctoral Scholar in the Space Structures Laboratory at Caltech\, condu cting research as part of the Space Solar Power Project (SSPP). He earned his Bachelor’s degree from Tel Aviv University\, and  his Master’s an d PhD degrees from the Technion.\n\n \;\n\nPlease be advised that all seminars scheduled for the near future\, and until further notice\, will b e held online only via Zoom. This transition allows us to maintain our aca demic calendar and ensure the safety and participation of our community re gardless of location. We are committed to ensuring these virtual sessions are delivered promptly and effectively. We appreciate your continued flexi bility and look forward to seeing you in our virtual seminars.\n Details: \n CATEGORIES:Seminars END:VEVENT BEGIN:VEVENT UID:0-1545@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260401T013000 DTEND;TZID=Asia/Jerusalem:20260401T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-04-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1546@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260406T013000 DTEND;TZID=Asia/Jerusalem:20260406T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-04-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1547@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260408T013000 DTEND;TZID=Asia/Jerusalem:20260408T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-04-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1548@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260413T013000 DTEND;TZID=Asia/Jerusalem:20260413T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-04-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1549@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260415T013000 DTEND;TZID=Asia/Jerusalem:20260415T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-04-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1550@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260420T013000 DTEND;TZID=Asia/Jerusalem:20260420T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-04-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1551@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260422T013000 DTEND;TZID=Asia/Jerusalem:20260422T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-04-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1552@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260427T013000 DTEND;TZID=Asia/Jerusalem:20260427T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-04-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1162@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260506T123000 DTEND;TZID=Asia/Jerusalem:20260506T143000 DTSTAMP:20260415T100313Z URL:https://aerospace.technion.ac.il/events/research-day-2026/ SUMMARY:Research Day 2026 DESCRIPTION:Lecturer:\n Faculty:The Stephen B. Klein Faculty of Aerospace E ngineering\n Institute:Technion – Israel Institute of Technology\n Locat ion:Faculty yard\n Zoom: \n Abstract: Our Graduate Studies Research Day is an annual event that attracts not only Aerospace Engineering students and faculty members but also students from around the campus and aerospace pr ofessionals from the industry. The graduate students will present their re search posters to the audience.\n\nAs part of the tradition\, a judging co mmittee chose the best posters of M.Sc. and Ph.D. students. In addition\, the crowd picked its favorite.\n\n\n Details: \n CATEGORIES:Events LOCATION:Faculty yard END:VEVENT BEGIN:VEVENT UID:0-1163@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260506T123000 DTEND;TZID=Asia/Jerusalem:20260506T143000 DTSTAMP:20260415T100253Z URL:https://aerospace.technion.ac.il/he/events/%d7%99%d7%95%d7%9d-%d7%94%d 7%9e%d7%97%d7%a7%d7%a8-2026/ SUMMARY:יום המחקר 2026 DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אווירונ וטיקה וחלל ע"ש סטיבן ב. קליין\n Institute:\n Locatio n:דשא הפקולטה להנדסת אוירונוטיקה וחלל\n Zoo m: \n Abstract: יום המחקר הפקולטי לתארים מתקדמי ם הוא אירוע שנתי שמושך לא רק סטודנטים וחב רי סגל להנדסת אוירונוטיקה וחלל\, אלא גם ס טודנטים מרחבי הקמפוס\, כמו גם אנשי מקצוע בתחום התעופה והחלל מהתעשייה. הסטודנטים ל תארים שני ודוקטורט מציגים את פרי המחקרים שלהם לקהל באירוע הפנינג שנתי גדול.\n\nכחל ק מהמסורת\, ועדת שיפוט בוחרת את המחקרים ה נבחרים. בנוסף\, הקהל מצביע ובוחר את המחקר חביב הקהל.\n\n\n Details: \n CATEGORIES:אירועים LOCATION:דשא הפקולטה להנדסת אוירונוטיקה וחלל END:VEVENT BEGIN:VEVENT UID:0-1629@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260506T133000 DTEND;TZID=Asia/Jerusalem:20260506T143000 DTSTAMP:20260316T091203Z URL:https://aerospace.technion.ac.il/events/resilient-decision-making-for- multi-robot-systems-in-the-presence-of-adversaries/ SUMMARY:Resilient Decision-Making for Multi-Robot Systems in the Presence o f Adversaries DESCRIPTION:Lecturer:Roee Francos\n Faculty:\n Institute:Harvard School of Engineering and Applied Sciences\n Location:Classroom 240\, Second Floor\, Aerospace Eng.\n Zoom: https://technion.zoom.us/j/98372598857\n Abstract: \n\n\nThis talk presents a unified perspective on resilient decision-maki ng for multi-robot systems operating in environments where adversaries may influence routing\, search\, and detection tasks. Over the past decade\, significant progress has been made in multi-robot systems research\, parti cularly in coordination\, control\, and navigation\, largely fueled by the rapid commercialization of unmanned aerial systems and drones. Yet\, depl oying these systems in real-world environments remains difficult. Most res earch assumes cooperative or optimally performing agents\, neglecting case s where agents behave adversarially or suboptimally due to uncertainty\, f aults\, or environmental disturbances. Resiliency to malicious or malfunct ioning agents remains a key limitation\, as such agents can degrade system efficiency and destabilize routing policies\, where stability is typicall y defined as bounded cost over time. Existing stability guarantees for coo perative fleets collapse when agents deviate from plans\, underscoring the need for adversarially aware planning and routing theory\, particularly i n safety-critical aerospace applications.\n\nIn my work\, I establish theo retical foundations for coordination\, control\, and learning under uncert ainty and adversarial influence\, focusing on routing and traffic manageme nt for fleets of aerial and ground agents\, with Urban Air Mobility as a c ompelling application. I develop adaptive algorithms that ensure provable stability\, resilience\, and safety.\n\nI will present new results on resi lient multi-agent policies that operate effectively despite adversaries in the decision loop\, including routing under adversarial influence from ag ents that manipulate data while remaining within the system.\n\nFinally\, I will show how resilient cooperative search strategies address challenges posed by intelligent\, coordinated external adversaries\, providing prova ble guarantees for coverage and detection in settings such as search and r escue and pursuit-evasion. I conclude by outlining future research directi ons at the intersection of safety\, learning\, and large-scale autonomy.\n \nRoee M. Francos is currently a Computer Science Postdoctoral Fellow at t he Robotics\, Embedded Autonomy\, and Communication Theory (REACT) Lab at Harvard University focusing on development of multi-agent resilient decisi on-making and coordination algorithms. In 2023\, he completed his PhD in C omputer Science at the Multi-Agent Robotic Systems Laboratory\, the Techni on-Israel Institute of Technology. He received the B.Sc. in Electrical and Computer Engineering from Ben-Gurion University. His research interests a re in multi-agent teamwork\, autonomous robotics\, intelligent transportat ion systems\, bio-inspired robotics and computer vision\, focusing on coll aborative algorithms for motion planning of autonomous vehicles\, multi-ro bot learning \, and air traffic management and coordination of unmanned ve hicles. Roee is a recipient of the 2023 Robotics Science and Systems (RSS) Pioneers Award and the 2025 IEEE Multi-Robot &\; Multi-Agent Systems ( MRS) Young Pioneer Award.\n\n \;\n\n\n\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:Classroom 240\, Second Floor\, Aerospace Eng. END:VEVENT BEGIN:VEVENT UID:0-1556@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260511T013000 DTEND;TZID=Asia/Jerusalem:20260511T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-05-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1648@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260511T133000 DTEND;TZID=Asia/Jerusalem:20260511T143000 DTSTAMP:20260415T085731Z URL:https://aerospace.technion.ac.il/events/geometric-analysis-and-optimiz ation-of-doppler-based-navigation-with-low-earth-orbit-satellites/ SUMMARY:Geometric Analysis and Optimization of Doppler-Based Navigation wit h Low Earth Orbit Satellites DESCRIPTION:Lecturer:Carlos Caravaca Gallego\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering\n Institute:Technion – Israel Institut e of Technology\n Location:Online Seminar via Zoom\n Zoom: https://technio n.zoom.us/j/94050711666\n Abstract: \n\n\nDoppler-only navigation using lo w-Earth orbit satellite constellations is a promising complement to Global Navigation Satellite Systems (GNSS)\, yet the geometric principles govern ing satellite selection for Doppler positioning differ fundamentally from those established for pseudorange-based navigation prevalent in GNSS. Volu me-based satellite selection\, effective for pseudorange-based geometric d ilution of precision (GDOP) minimization\, shows weak correlation with Dop pler GDOP\, but the mechanism responsible for this failure has not been id entified thus far. In this talk\, we will develop the theoretical framewor k needed to explain this phenomenon. Analytical parameterization of the ei ght-state Doppler Jacobian measurement matrix reveals that clock bias sens itivity creates a functional collinearity with the vertical-velocity colum n\, which has no pseudorange analogue\, and cannot be eliminated by any ge ometric arrangement. A Schur-complement framework quantifies the resulting covariance inflation\, and a systematic experimental campaign validates t he predictions\, confirming that altitude diversity is the primary decorre lation mechanism. The main contribution is the analysis and explanation of why volume-based satellite selection fails\, and why common heuristic GDO P proxies remain limited in effectiveness. Implications for optimal satell ite selection for Doppler-based navigation are outlined.\n\n \;\n\nThi s work is towards a Ph.D. degree under the supervision of Prof. Pini Gurfi l\, Shirley and Burt Harris Professor of Aerospace Engineering.\nCoadvisor : Dr. Hector Rotstein\, Research Fellow\, Department of Computer Science\, The Technion\n\n \;\n\n \;\n\nPlease be advised that all seminars scheduled for the near future\, and until further notice\, will be held o nline only via Zoom. This transition allows us to maintain our academic ca lendar and ensure the safety and participation of our community regardless of location. We are committed to ensuring these virtual sessions are deli vered promptly and effectively. We appreciate your continued flexibility a nd look forward to seeing you in our virtual seminars.\n\n \;\n\n\n\n Details: \n CATEGORIES:Seminars LOCATION:Online Seminar via Zoom END:VEVENT BEGIN:VEVENT UID:0-1557@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260513T013000 DTEND;TZID=Asia/Jerusalem:20260513T023000 DTSTAMP:20251118T063840Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-05-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1558@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260518T013000 DTEND;TZID=Asia/Jerusalem:20260518T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-05-18/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1559@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260520T013000 DTEND;TZID=Asia/Jerusalem:20260520T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-05-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1636@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260520T123000 DTEND;TZID=Asia/Jerusalem:20260520T143000 DTSTAMP:20260121T131821Z URL:https://aerospace.technion.ac.il/events/faculty-picnic-2026/ SUMMARY:Faculty Picnic 2026 DESCRIPTION:Lecturer:\n Faculty:The Stephen B. Klein Faculty of Aerospace E ngineering\n Institute:\n Location:Faculty yard\n Zoom: \n Abstract: \n De tails: \n The students’ annual event\n CATEGORIES:Events LOCATION:Faculty yard END:VEVENT BEGIN:VEVENT UID:0-1639@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260520T123000 DTEND;TZID=Asia/Jerusalem:20260520T143000 DTSTAMP:20260121T133135Z URL:https://aerospace.technion.ac.il/he/events/%d7%94%d7%a4%d7%99%d7%a7%d7 %a0%d7%99%d7%a7-%d7%94%d7%a4%d7%a7%d7%95%d7%9c%d7%98%d7%99-2026/ SUMMARY:הפיקניק הפקולטי 2026 DESCRIPTION:Lecturer:\n Faculty:הפקולטה להנדסת אווירונ וטיקה וחלל ע"ש סטיבן ב. קליין\n Institute:\n Locatio n:מדשאת הפקולטה\n Zoom: \n Abstract: \n Details: \n האירו ע המרכזי של הסטודנטים להנדסת אווירונוטי קה וחלל!\n\n \;\n\n CATEGORIES:אירועים LOCATION:מדשאת הפקולטה END:VEVENT BEGIN:VEVENT UID:0-1560@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260525T013000 DTEND;TZID=Asia/Jerusalem:20260525T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-05-25/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1561@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260527T013000 DTEND;TZID=Asia/Jerusalem:20260527T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-05-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1562@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260601T013000 DTEND;TZID=Asia/Jerusalem:20260601T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-06-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1645@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260603T113000 DTEND;TZID=Asia/Jerusalem:20260603T143000 DTSTAMP:20260316T091223Z URL:https://aerospace.technion.ac.il/events/the-aeroservoelasticity-of-hig h-aspect-ratio-wings-with-many-control-surfaces-recent-progress-2/ SUMMARY:Phononic crystals for passive hypersonic flow control DESCRIPTION:Lecturer:Pavel Galich\n Faculty:The Stephen B. Klein Faculty of Aerospace Engineering \n Institute:Technion – Israel Institute of Techn ology\n Location:TBA\n Zoom: https://technion.zoom.us/j/98372598857\n Abst ract: TBA\n Details: \n CATEGORIES:Seminars,סמינרים LOCATION:TBA END:VEVENT BEGIN:VEVENT UID:0-1564@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260608T013000 DTEND;TZID=Asia/Jerusalem:20260608T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-06-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1565@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260610T013000 DTEND;TZID=Asia/Jerusalem:20260610T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-06-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1566@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260615T013000 DTEND;TZID=Asia/Jerusalem:20260615T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-06-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1567@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260617T013000 DTEND;TZID=Asia/Jerusalem:20260617T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-06-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1568@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260622T013000 DTEND;TZID=Asia/Jerusalem:20260622T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-06-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1569@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260624T013000 DTEND;TZID=Asia/Jerusalem:20260624T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-06-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1570@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260629T013000 DTEND;TZID=Asia/Jerusalem:20260629T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-06-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1571@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260701T013000 DTEND;TZID=Asia/Jerusalem:20260701T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-01/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1572@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260706T013000 DTEND;TZID=Asia/Jerusalem:20260706T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-06/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1573@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260708T013000 DTEND;TZID=Asia/Jerusalem:20260708T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-08/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1574@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260713T013000 DTEND;TZID=Asia/Jerusalem:20260713T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-13/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1575@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260715T013000 DTEND;TZID=Asia/Jerusalem:20260715T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-15/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1576@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260720T013000 DTEND;TZID=Asia/Jerusalem:20260720T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-20/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1577@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260722T013000 DTEND;TZID=Asia/Jerusalem:20260722T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-22/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1578@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260727T013000 DTEND;TZID=Asia/Jerusalem:20260727T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-27/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1579@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260729T013000 DTEND;TZID=Asia/Jerusalem:20260729T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-07-29/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1580@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260803T013000 DTEND;TZID=Asia/Jerusalem:20260803T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-03/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1581@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260805T013000 DTEND;TZID=Asia/Jerusalem:20260805T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1582@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260810T013000 DTEND;TZID=Asia/Jerusalem:20260810T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-10/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1583@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260812T013000 DTEND;TZID=Asia/Jerusalem:20260812T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1584@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260817T013000 DTEND;TZID=Asia/Jerusalem:20260817T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-17/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1585@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260819T013000 DTEND;TZID=Asia/Jerusalem:20260819T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1586@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260824T013000 DTEND;TZID=Asia/Jerusalem:20260824T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-24/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1587@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260826T013000 DTEND;TZID=Asia/Jerusalem:20260826T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1588@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260831T013000 DTEND;TZID=Asia/Jerusalem:20260831T023000 DTSTAMP:20251118T063839Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-08-31/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1589@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260902T013000 DTEND;TZID=Asia/Jerusalem:20260902T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-02/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1590@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260907T013000 DTEND;TZID=Asia/Jerusalem:20260907T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1591@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260909T013000 DTEND;TZID=Asia/Jerusalem:20260909T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1592@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260914T013000 DTEND;TZID=Asia/Jerusalem:20260914T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1593@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260916T013000 DTEND;TZID=Asia/Jerusalem:20260916T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-16/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1594@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260921T013000 DTEND;TZID=Asia/Jerusalem:20260921T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1595@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260923T013000 DTEND;TZID=Asia/Jerusalem:20260923T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-23/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1596@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260928T013000 DTEND;TZID=Asia/Jerusalem:20260928T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-28/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1597@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20260930T013000 DTEND;TZID=Asia/Jerusalem:20260930T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-09-30/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1598@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261005T013000 DTEND;TZID=Asia/Jerusalem:20261005T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-10-05/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1599@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261007T013000 DTEND;TZID=Asia/Jerusalem:20261007T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-10-07/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1600@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261012T013000 DTEND;TZID=Asia/Jerusalem:20261012T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-10-12/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1601@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261014T013000 DTEND;TZID=Asia/Jerusalem:20261014T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-10-14/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1602@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261019T013000 DTEND;TZID=Asia/Jerusalem:20261019T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-10-19/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1603@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261021T013000 DTEND;TZID=Asia/Jerusalem:20261021T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-10-21/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1604@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261026T013000 DTEND;TZID=Asia/Jerusalem:20261026T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-10-26/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: 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URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-11-04/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1608@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261109T013000 DTEND;TZID=Asia/Jerusalem:20261109T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-11-09/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT UID:0-1609@aerospace.technion.ac.il DTSTART;TZID=Asia/Jerusalem:20261111T013000 DTEND;TZID=Asia/Jerusalem:20261111T023000 DTSTAMP:20251118T063838Z URL:https://aerospace.technion.ac.il/events/seminar-slot-2026-11-11/ SUMMARY:Seminar Slot DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra ct: \n Details: \n CATEGORIES:Seminars Slots END:VEVENT BEGIN:VEVENT 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