摘要
针对航天器在轨运行时受到外部干扰以及存在执行机构部分失效故障的问题,提出一种基于自适应滑模控制的鲁棒容错控制方法.该方法利用自适应算法估计执行机构故障的最小值,并通过设计滑模变结构控制器来实现对故障的容错控制以及对干扰的抑制控制,无需精确获得执行机构故障值,从而使得设计的控制器对于故障具有一定的鲁棒性.仿真结果表明了该方法对于姿态调节过程中执行机构部分失效故障具有较强的容错能力.
A method of robust fault tolerant attitude control, based on adaptive sliding mode control is proposed for an on-orbiting spacecraft in the presence of partial loss of actuator effectiveness and external disturbance. In this approach, adaptive technique is employed to estimate the minimum value of actuator fault, and a sliding mode attitude controller is then designed to achieve fault tolerant control and external disturbance rejection. For the designers, the real minimum value of the fault is not required to be known in advance exactly, and the great robustness to fault is guaranteed. The simulation results of an application to spacecraft attitude adjustment maneuver show that great fault tolerant capability can be achieved even under partial loss of actuator effectiveness.
出处
《控制与决策》
EI
CSCD
北大核心
2011年第6期801-805,共5页
Control and Decision
基金
国家自然科学基金项目(61004072)
高等学校博士学科点专项科研基金项目(20070213061)
黑龙江省留学回国人员科学基金项目(LC08C01)
哈尔滨市科技创新人才研究专项基金项目(2010RFLXG001)
关键词
航天器
部分失效故障
容错控制
滑模控制
spacecraft
partial loss of actuator effectiveness
fault tolerant
sliding mode control
