摘要
研究了基于时间尺度分离和滑动模态的航天器姿态控制问题.利用时间尺度分离的方法将航天器状态分成对应于姿态角的慢子系统和对应于姿态角速度的快子系统,从而构成内外两个控制回路,外回路跟踪给定的姿态角,内回路跟踪设计的姿态角速度.针对每个子系统分别设计PI型的滑动平面,在Lyapunov稳定性分析的基础上,推导出两个回路的变结构控制律.仿真结果证明了所提控制方法能够克服大幅值、高频率的外部干扰,比传统控制方法具有更高的精度和鲁棒性.
The states of spacecraft are divided into two subsystems based on the time-scale principle. A two-loop sliding mode controller is achieved, with the outer loop tracking the given attitude angles and the inner loop tracking the designed angular velocities. For each of the subsystems, a variable structure controller is constructed respectively. A PI sliding surface is designed; and a variable control law is obtained according to Lyapunov stability analysis. Simulation results show that the two-loop sliding mode controller has a higher precision and a better robustness than the traditional PID controller.
出处
《武汉大学学报（工学版）》
CAS
CSCD
北大核心
2007年第6期117-121,共5页
Engineering Journal of Wuhan University
基金
教育部博士点基金(编号:20030287008)
南京航空航天大学青年科研基金(编号:1003-274004)资助项目
关键词
变结构控制
滑动模态
时间尺度
姿态控制
variable structure control
sliding mode
time scale
attitude control
