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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.

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