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UID:0-1601@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20261014T133000

DTEND;TZID=Asia/Jerusalem:20261014T143000

DTSTAMP:20260922T113819Z

URL:https://aerospace.technion.ac.il/events/seminar-14oct2026-bar-gawi/

SUMMARY:Robust Control of a Hypersonic Gliding Vehicle with Significant Mod
 el Uncertainties
DESCRIPTION:Lecturer:Bar Gawi\n Faculty:The Stephen B. Klein Faculty of Aer
 ospace Engineering\n Institute:Technion – Israel Institute of Technology
 \n Location:Classroom 240\, 1st floor\, Aerospace Eng. building\n Zoom: ht
 tps://technion.zoom.us/j/98372598857\n Abstract: \n\n\nHypersonic gliding 
 vehicles (HGVs) operate in flight regimes characterized by nonlinear dynam
 ics\, significant aerodynamic uncertainties\, and strong coupling between 
 vehicle motions. These characteristics pose challenges for flight control 
 design\, particularly when tracking performance must be maintained despite
  model inaccuracies\, changing flight conditions\, and practical implement
 ation limitations. This work addresses robust flight control of an HGV\, w
 ith emphasis on acceleration tracking under aerodynamic model uncertainty.
 \nA nonlinear six-degree-of-freedom model serves as the basis for simulati
 on and controller evaluation. Control-oriented linear models are derived a
 round selected operating conditions\, while uncertain aerodynamic paramete
 rs are represented explicitly in an affine form within a structured uncert
 ainty framework. This formulation enables the application of H-infinity an
 d structured singular value (μ-synthesis) methods for controller synthesi
 s and robustness analysis.\n\nThe control design incorporates actuator and
  sensor dynamics\, together with frequency-dependent weighting functions t
 hat shape tracking performance\, improve transient response\, and limit co
 ntrol effort. The weights also address elastic modes through frequency sha
 ping\, without explicitly including aeroelastic dynamics in the synthesis 
 model\, thereby simplifying the model and controller design. Practical imp
 lementation aspects are examined through discrete-time synthesis and contr
 oller-order reduction.\n\nClosed-loop performance is evaluated through fre
 quency-domain analysis\, linear time responses\, and nonlinear Monte Carlo
  simulations with uncertain aerodynamic parameters. Aeroelastic modes are 
 incorporated into the nonlinear simulations to assess their influence on c
 losed-loop behavior. The results demonstrate stable responses and effectiv
 e reference tracking across the tested cases\, supporting the applicabilit
 y of the linear-model-based controllers to the nonlinear vehicle despite a
 erodynamic uncertainties and aeroelastic effects.\n\nThis work is towards 
 an M.Sc. degree under the supervision of Prof. Moshe Idan and Dr. Oded Gol
 an\, The Stephen B. Klein Faculty of Aerospace Engineering\, Technion.\n\n
 \n\n Details: \n 
CATEGORIES:Seminars
LOCATION:Classroom 240\, 1st floor\, Aerospace Eng. building

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