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Precision attitude regulation of uncertain flexible spacecraft
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Consider the precision attitude regulation with vibration suppression for an uncertain and disturbed flexible spacecraft.The disturbance at issue is typically any finite superposition of sinusoidal signals with unknown frequencies and step signals of unknown amplitudes.First we show that the conventional mathematical model for flexible spacecrafts is transformable to a multi-input multi-output(MIMO)strict-feedback nonlinear normal form.Particularly it is strongly minimum-phase and has a well-defined uniform vector relative degree.Then it enables us to develop an adaptive internal model-based controller in the framework of adaptive output regulation to solve the problem.It is proved that asymptotic stability can be guaranteed for the attitude regulation task and the vibration of flexible appendages vanishes asymptotically.Hence,the present study explores a new idea for control of flexible spacecraft in virtue of its system structures.
Flexible spacecraftDisturbance rejectionInternal model principleAttitude regulation
Haiwen Wu、Xinghu Wang、Andong Sheng、Dabo Xu
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School of Automation,Nanjing University of Science and Technology,Nanjing 210094,Jiangsu,China
Department of Automation,University of Science and Technology of China,Hefei 230027,Anhui,China
Shien-Ming Wu School of Intelligent Engineering,South China University of Technology,Guangzhou 511442,Guangdong,China
National Natural Science Foundation of ChinaNational Natural Science Foundation of ChinaNational Natural Science Foundation of China
NETL
NSTL
万方数据
维普
