학술논문
On-Line Computation of a Local Attainable Moment Set for Reusable Launch Vehicles
Document Type
Report
Author
Source
Subject
Language
English
Abstract
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].