卫星姿态控制系统执行器故障检测与分离  

Actuator fault detection and isolation for the attitude control system of satellite

作　　者：王振华[1] 张淼[1] 沈毅[1] 

机构地区：[1]哈尔滨工业大学控制科学与工程系,哈尔滨150001

出　　处：《哈尔滨工业大学学报》2013年第2期72-76,共5页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金委创新研究群体科学基金资助项目(61021002);中央高校基本科研业务费专项资金资助项目(HIT.KLOF.2011071)

摘　　要：针对卫星姿态控制系统,提出一种基于未知输入观测器的执行器故障检测与分离方法.通过将指定的故障视为未知输入,设计未知输入观测器使得残差向量对指定的故障不敏感,同时保持对其他故障的敏感性,从而实现执行器故障的检测与分离.本文将未知输入观测器设计问题转化为一组线性矩阵不等式(LMI),可以通过LMI工具箱方便地求解.最后,将所提出的方法用于卫星姿态控制系统,仿真结果表明了该方法能快速准确地诊断执行器故障.This paper proposes an actuator fault diagnosis approach based on unknown input observers for the attitude control system of satellite. More specifically, by considering an actuator fault as the unknown input vector, an unknown input observer is designed so that the residual is sensitive to the other faults while insensitive to the appointed one. In this work, the design of unknown input observer is formulated as a set of linear matrix inequality （LMI）, which can be solved by the LMI toolbox conveniently. Finally, the proposed approach is applied to the satellite attitude control system. Simulation examples illustrate the presented method is able to detect and isolate the actuator fault effectively.

关 键 词：姿态控制系统 故障检测与分离 线性矩阵不等式 未知输入观测器 卫星 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]