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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

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