摘要
研究了挠性航天器的姿态控制器设计问题。结合Lyapunov矩阵成形的不变椭圆,使用多目标综合技术集成干扰抑制,鲁棒稳定和控制输入约束问题。基于迭代的线性矩阵不等式(ILMI)给出了静态输出反馈控制器。仿真结果表明,该方法虽然具有一定的保守性,但可以较好的满足系统的鲁棒性能要求,对工程实现具有一定的参考价值。
The design problem of attitude controller for the flexible spacecraft is presented.Within the invariant ellipsoid shaped by Lyapunov matrix,disturbances attenuation,robust stabilization and constrains on the control input is incorporated for the uncertain system using multiobjective synthesis approach.The static output feedback controller is obtained based on an iterative algorithm of Linear Matrix Inequalities(LMIs).Our approach,while conservative,can meet the system performance and design specifications w...
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2007年第3期539-544,共6页
Journal of Astronautics
关键词
线性矩阵不等式
挠性航天器
静态输出
输入饱和
Linear matrix inequality
Flexible spacecraft
Static output
Input saturation
