Adaptive Integral-type Sliding Mode Control for Spacecraft Attitude Maneuvering Under Actuator Stuck Failures

被引:53
|
作者
Hu Qinglei [1 ,2 ]
Zhang Youmin [2 ]
Huo Xing [1 ]
Xiao Bing [1 ]
机构
[1] Harbin Inst Technol, Dept Control Sci & Engn, Harbin 150001, Peoples R China
[2] Concordia Univ, Dept Mech & Ind Engn, Montreal, PQ H3G 2W1, Canada
基金
中国国家自然科学基金; 高等学校博士学科点专项科研基金;
关键词
integral sliding mode control; attitude maneuvering; stuck failure; adaptive control; spacecraft; FAULT-TOLERANT CONTROL; VARIABLE-STRUCTURE CONTROL; OUTPUT-FEEDBACK CONTROL; FLEXIBLE SPACECRAFT; TRACKING CONTROL; CONTROL-SYSTEM; PERFORMANCE; SATELLITES; DIAGNOSIS; DESIGN;
D O I
10.1016/S1000-9361(11)60005-8
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
A fault tolerant control (FTC) design technique against actuator stuck faults is investigated using integral-type sliding mode control (ISMC) with application to spacecraft attitude maneuvering control system. The principle of the proposed FTC scheme is to design an integral-type sliding mode attitude controller using on-line parameter adaptive updating law to compensate for the effects of stuck actuators. This adaptive law also provides both the estimates of the system parameters and external disturbances such that a prior knowledge of the spacecraft inertia or boundedness of disturbances is not required. Moreover, by including the integral feedback term, the designed controller can not only tolerate actuator stuck faults, but also compensate the disturbances with constant components. For the synthesis of controller, the fault time, patterns and values are unknown in advance, as motivated from a practical spacecraft control application. Complete stability and performance analysis are presented and illustrative simulation results of application to a spacecraft show that high precise attitude control with zero steady-error is successfully achieved using various scenarios of stuck failures in actuators.
引用
收藏
页码:32 / 45
页数:14
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