Traditional attitude control design of reusable launch vehicles involves independent design of autopilot and control allocation modules [SBB99], [SK97], [SHJ00], [PS00], [Hod00]. Unfortunately, this results in the potential for overly aggressive commands in the autopilot resulting in a loss of performance due to actuator saturation, particularly if the autopilot may suffer from integrator wind-up [HH01].
On-Line Computation of a Local Attainable Moment Set for Reusable Launch Vehicles
2002 AIAA GN and C Conference ; 2002 ; Monterey, CA, United States
2002-01-09
Preprint
Keine Angabe
Englisch
AIAA-2002-4780 On-Line Computation of a Local Attainable Moment Set for Reusable Launch Vehicles
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