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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.

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