一种针对卫星执行机构故障的容错控制系统  

A fault-tolerant control system to handle actuator failures of a satellite

作　　者：梁津津[1] 王青[1] 董朝阳[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：《华中科技大学学报（自然科学版）》2009年第S1期267-270,共4页Journal of Huazhong University of Science and Technology(Natural Science Edition)

摘　　要：针对卫星执行机构故障的容错控制问题,提出了一种基于模糊全局动态变结构的容错姿态控制系统.通过在滑模面引入输入量,减少了滑模控制中的抖振;通过设计全局滑模面以确保系统响应对系统不确定性(执行机构故障)和外部干扰具有全局鲁棒性,从而确保系统在故障处理期间的稳定性;通过切换分配矩阵来保证故障处理后系统仍具有好的动态性能.采用4个反作用飞轮结构进行姿态控制,将卫星姿态控制所需的力矩分配给4个飞轮,给出了执行机构故障情况下分配矩阵的计算公式,证明了设计的控制律算法的稳定性.通过仿真证明了该控制律对卫星非线性模型具有较高的控制精度,并且对系统模型干扰和外界干扰有很强的鲁棒性.A fault-tolerant attitude control system was proposed for a satellite based on fuzzy global dynamic sliding mode control(FGDSMC) algorithm.To solve the steep problem of the sliding mode control algorithm,the input signal was added to the sliding mode.By designing a global dynamic sliding surface,this controller can ensure that the response of the system has global robustness against to the uncertainties of system(actuator failure) and external disturbances.When fault occurs,this robustness can make ensure the system is stable during the fault management period and the switch of the arrangement matrix can ensure the excellent response performances.The formulation of the arrangement matrix was provided.We proved the stability of the designed control law,and simulated the attitude control system.The simulation results show that the attitude control law has high accuracy and robustness.

关 键 词：卫星 姿态控制 全局动态滑模控制 容错控制 模糊 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]