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
5 pages
Report
No indication
English
AIAA-2002-4780 On-Line Computation of a Local Attainable Moment Set for Reusable Launch Vehicles
British Library Conference Proceedings | 2002
|Engineering Index Backfile | 1964
|Reusable Launch Vehicles Outlook - Launch Vehicles Table
Online Contents | 2009