基于积分滑模的航天器有限时间姿态容错控制
Integral-type sliding mode finite-time fault tolerant control for

针对存在执行机构故障和外部干扰的刚体航天器姿态稳定系统, 本文提出了基于积分滑模的容错控制策 略, 实现了姿态有限时间稳定. 首先, 利用齐次系统相关理论, 设计了一类饱和有界的基础控制律, 保证了不存在执 行机构故障和干扰情况下的姿态有限时间稳定. 在此基础上, 利用积分滑模和自适应技术设计了一种有限时间姿 态鲁棒容错控制方案, 对执行机构故障和干扰进行有效的补偿; 该方案能够快速地实现姿态高精度稳定, 并抑制系 统抖振现象. 最后, 将本文提出的姿态容错控制方案进行数值仿真与对比, 验证了方案的有效性与优越性.
This paper addresses the problem of integral-type sliding mode robust fault tolerant control for spacecraft , in the presence of actuator failures and external disturbances simultaneously, achieving the finite-time attitude stabilization. As a stepping stone, a simple saturated nominal controller is firstly designed using homogeneous system theory, to ensure finite-time attitude stabilization of spacecraft without failures and disturbances. Then, utilizing integral-type sliding mode and adaptive techniques, a novel finite-time robust fault tolerant control strategy is developed to compensate for actuators failures and external disturbances. And also, the chattering problem has been restrained via a gain adjusting law. Finally, numerical simulation results are presented to illustrate and highlight the fine performance benefits obtained using the proposed scheme, especially for the faster and higher-precise attitude stabilization.