摘要
研究机动再入飞行器的制导控制问题。为了解决机动再入飞行器气动系数变化范围大、气动耦合严重和气动参数非线性过零常值大等恶劣条件下的控制 ,并且能充分利用飞行器可测量信息提高系统自适应能力 ,本文提出了状态方程参数辨识—极点配置—前馈补偿自适应控制的飞行控制系统的设计方法。通过对新型号再入飞行器的制导系统仿真 。
The guidance and control are discussed for the maneuvering reentry vehicles,which are under severe conditions such as pneumatically heavy coupling and wide range of aerodynamic parameter change.In order to improve the adaptation property of the system by using the available information, a design method for flight control system is proposed.This method yields a feedforward compensated adaptive control based on both parameter identification for the state equation and Pole assignment.The simulation shows that the proposed design method provides a good flight performance for vehicles.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2002年第1期40-45,共6页
Journal of Astronautics
基金
中国博士后科学基金资助 (2 0 0 0年度 )
