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Fault-tolerant control and vibration suppression of flexible spacecraft:An interconnected system approach

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This paper considers a fault-tolerant control and vibration suppression problem of flex-ible spacecraft. The attitude dynamics is modeled by an interconnected system, in which the rigid part and the flexible part are coupled with each other. Such a model allows us to use the intercon-nected system approach to analyze the flexible spacecraft. Both distributed and decentralized observer-based fault-tolerant control schemes are developed, under which the closed-loop stability of flexible spacecraft can be ensured by using the cycle-small-gain theorem. Compared with the tra-ditional method, this paper considers the faults occurred not only in the rigid parts, but also in the flexible parts. In addition, the application of the interconnected system approach simplifies the sys-tem model of flexible spacecraft, thereby the difficulty of theoretical analysis and engineering prac-tice of fault-tolerant control of flexible spacecraft are greatly reduced. Simulation results show the effectiveness of the proposed methods and the comparison of different fault-tolerant control approach.

Cycle-small-gain theoremDecentralized fault-tolerant controlDistributed fault-tolerant controlFlexible spacecraftInterconnected system

Qian LI、Hao YANG、Dong ZHAO、Bin JIANG

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College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China

This work is supported by National Natural Science Foundation of ChinaThis work is supported by National Natural Science Foundation of ChinaNatural Science Foundation of Jiangsu Province, Chinaand Fundamental Research Funds for the Central Universities, China

Nos. 6162230461773201 BK20160035 NE2015002

2020

中国航空学报(英文版)
中国航空学会

中国航空学报(英文版)

CSTPCDCSCDSCIEI
影响因子：0.847
ISSN：1000-9361
年,卷(期)：2020.33(7)
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