执行器跳变故障的失效卫星轨迹跟踪控制  

Trajectory tracking control of failure satellite with actuator jumping fault

作　　者：路阳 蔡彬 乔道鹏 付艳明[1] 张卯瑞[1] LU Yang;CAI Bin;QIAO Daopeng;FU Yanming;ZHANG Maorui(Center for Control Theory and Guidance Technology, Harbin Institute of Technology, Harbin 150001, China;Beijing Institute of Electronic System Engineering, Beijing 100854, China)

机构地区：[1]哈尔滨工业大学控制理论与制导技术研究中心,黑龙江哈尔滨150001 [2]北京电子工程总体研究所,北京100854

出　　处：《西北工业大学学报》2022年第2期458-464,共7页Journal of Northwestern Polytechnical University

摘　　要：研究了执行器跳变故障的失效卫星轨迹跟踪控制问题,提出了具有跳变控制输入的模型参考跟踪控制器设计方法。结合随机稳定和模型参考跟踪定义,给出了失效卫星轨迹跟踪控制的问题描述。同时考虑系统存在扰动以及推力受限情形,利用线性矩阵不等式方法和非齐次广义Sylvester矩阵方程的参数化解方法,分别设计了对干扰具有抑制效果的鲁棒H_(∞)状态反馈控制律和完全参数化形式的前馈补偿器。将所提出的方法应用于卫星在轨交会控制系统的控制器设计,仿真结果验证了所提方法的有效性。This paper studied the trajectory tracking control of a failure satellite that has actuator jumping fault.It proposed a design method based on the jumping control input for the model reference tracking controller.By comb-ining the stochastic stability definition with model reference tracking,it gave the mathematical descriptions of the trajectory tracking control of the failure satellite.It used the linear matrix inequality method and the parametric solution method of the nonhomogeneous generalized Sylvester matrix equation to design the robust H_(∞) state feedback control law and the complete parametric feed-forward tracking compensator respectively,with the disturbance of the failure satellite and its thrust constraint considered simultaneously.The numerical simulation results on the model of the satellite rendezvous system show that the design method proposed in this paper is effective.

关 键 词：跳变故障 失效卫星 模型参考跟踪 参数化方法 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]