基于LMI的挠性航天器抗饱和补偿器设计及分析  

The Anti-windup Compensator Design and Analysis for the Flexible Spacecraft Based on the LMI Method

作　　者：王明钊[1] 刘金琨[1] 

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100191

出　　处：《航天控制》2014年第1期63-67,共5页Aerospace Control

基　　金：国家自然科学基金项目(61374048);高效博士点基金项目(20121102110008)

摘　　要：针对挠性航天器中输入受限问题,设计了基于LMI的抗饱和补偿器。理想情况下,挠性航天器采用LQG控制,保持系统闭环稳定;输入受限时,在不改变系统原有结构的前提下,设计基于LMI的抗饱和补偿器。抗饱和补偿器为静态补偿器,所以不增加系统阶数;它不仅保证系统能够闭环稳定,还能保证系统满足最优的L2指标。仿真表明,在理想情况和受限情况下,抗饱和补偿器均能保证系统闭环稳定,并且具有良好的鲁棒性。An anti-windup compensator based on the linear matrix inequalities （LMI） is design for the input saturation in controlling the flexible spacecraft.The LQG controller can guarantee the stability of the close-loop system in the ideal condition but in the input saturation condition.Therefore,the compensator based on the LMI is designed.The compensator,which is state without increasing the system order,can guarantee both the stability of the close-loop system and the optimal L2 performance of the system.The simulation results show that the compensator can guarantee the close-loop stability and robustness not only in the ideal condition but also in the input saturation condition.

关 键 词：输入受限 LMI 抗饱和 挠性航天器 补偿器 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]