卫星姿态控制系统的可重构性分析  

Reconfigurability Analysis for Satellite Attitude Control Systems

作　　者：樊雯[1] 程月华[2] 姜斌[1] 刘文静[3,4] 

机构地区：[1]南京航空航天大学自动化学院,南京210016 [2]南京航空航天大学航天学院,南京210016 [3]北京控制工程研究所,北京100190 [4]空间智能控制技术国家级重点实验室,北京100190

出　　处：《宇航学报》2014年第2期185-191,共7页Journal of Astronautics

基　　金：国家自然科学基金(61273171;61203091);973计划项目(973-613156);上海航天科技创新基金(SAST201234)

摘　　要：针对执行机构和传感器故障情况,将可重构性的概念引入卫星姿态控制系统,并提出可重构性评价方案来分析某一配置下的卫星姿态控制系统的在轨可重构性。首先,针对线性化系统模型,根据执行机构配置分析故障后系统的可控性及控制能耗,并利用可控性格兰姆矩阵的最小特征值给出系统的可重构性度量指标。其次,针对某一传感器配置,从系统级的角度分析系统的可观性与可重构性之间的关系。在此基础上,给出整个卫星姿态控制系统的可重构性评价方案。最后针对某一配置的卫星姿态控制系统模型进行仿真分析,说明该方案的有效性。Reconfigurability represents the potential of the system to tolerate faults with resources constraints. In this paper, an approach is proposed to evaluate and analyze the reeonfigurability of satellite attitude control systems （ACS） with respect to actuator and sensor faults under a certain configuration. First, based on the common actuator configuration of ACS, controllability and control energy consumption of post-fault system are analyzed for the linearized system model. And the smallest eigenvalue of controllability Gram matrix is utilized to measure the level of reconfigurability. Then the relationship between observability and reconfigurability is discussed from the system point of view for a certain sensor configuration. Based on the analysis, an approach to assess the whole ACS＇ s reeonfigurability is presented. Simulation results are given to demonstrate the effectiveness of the proposed approach.

关 键 词：卫星姿态控制系统 可重构性 容错控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]