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

ISSN号：1000-9361
期刊名称：《中国航空学报：英文版》
时间：0
分类：TP273[自动化与计算机技术—控制科学与工程;自动化与计算机技术—检测技术与自动化装置] TP393.4[自动化与计算机技术—计算机应用技术;自动化与计算机技术—计算机科学与技术]
作者机构：[1]Department of Control Science and Engineering, Harbin Institute of Technology, Harbin 150001, China, [2]Department of Mechanical and Industrial Engineering, Concordia University, Montreal H3G 2W1, Canada
相关基金：National Natural Science Foundation of China（61004072）; Fundamental Research Funds for the Central Universities（HIT.NSRIF.2009003）; Research Fund for the Doctoral Program of Higher Education of China （20070213061 20102302110031）; Scientific Research Foundation for the Returned Overseas Chinese Scholars of Harbin （2010RFLXG001）

作者： HU Qinglei[1,2], ZHANG Youmin[2], HUO Xing[1], XIAO Bing[1]

关键词：执行器故障, 自适应更新, 滑模控制, 姿态机动, 航天器, 积分型, 姿态控制器, 滞留, integral sliding mode control, attitude maneuvering, stuck failure, adaptive control, spacecraft

中文摘要：

对粘住的致动器的容忍的控制(FTC ) 设计技术指责的一个差错用申请用不可分类型的滑动模式控制(ISMC ) 被调查到调遣控制系统的太空船态度。建议 FTC 计划的原则是用联机参数设计一个不可分类型的滑动模式态度控制器适应的更新法律补偿粘住的致动器的效果。这条适应法律也两个都规定系统参数和外部骚乱的估计以便太空船惯性的优先的知识或骚乱的固定没被要求。而且由包括不可分的反馈术语，设计控制器不能仅仅容忍，致动器粘住差错，而且与经常的部件补偿骚乱。预先为控制器，差错时间，模式和值的合成是未知的从一个实际太空船控制应用程序激发了。完全的稳定性和表演分析被介绍，到一只太空船的申请的解说性的模拟结果显示出那高精确的态度控制与零稳定错误成功地在致动器用粘住的失败的各种各样的情形被完成。

英文摘要：

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.

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