摘要
基于Ｈ∞控制和状态观测器理论，提出了对部分执行器失效具有Ｈ∞范数界的容错控制器设计方法，并成功地应用于某飞行器姿态系统部分执行器失效容错控制中，理论分析和实例设计验证了该方法的有效性。
We Chinese engineers have found some technical information in the open literature on how to keep flight vehicle working when partial failure of actuator occurs. We find it possible to meet China′s needs better by using a faulttolerent controller designed by us to keep the performance of such a flight vehicle fairly good. The heart of the principles underlying the faulttolerent controller designed by us is Theorem 1. Proof of Theorem 1 and its discussion take up considerible space, starting with eq.(10) and ending at eq.(23). Eqs.(10) through (13) are particularly important. We took as an example for numerical simulation the attitude control system of a certain type of Chinese flight vehicle. Figs.1 and 2 show the calculated results of numerical simulation. They show clearly that fairly good stability is retained. Furthermore, on the basis of simulation calculations, we computed the closed[CD*2]loop system performance H ∞ norm bound to be 2.890. All these appear to confirm that fairly good performance is retained even when partial failure of actuator occurs.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
1997年第4期563-569,共7页
Journal of Northwestern Polytechnical University
基金
国家教委博士点基金
