Attitude Synchronization of Rigid Spacecraft Using Terminal Sliding Mode

Zhou Ning; Xia Yuanqing; Lu Kunfeng

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Attitude Synchronization of Rigid Spacecraft Using Terminal Sliding Mode

Zhou Ning,Xia Yuanqing *,Lu Kunfeng

School of Automation, Beijing Institute of Technology, Beijing 100081

*Correspondence author

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Funding: The workof Yuanqing Xia was supported by the National Basic Research Programof China (973 Program) （No.2012CB720000）, the National Natural Science Foundation of China（No.61225015,60974011）, the Ph.D.Programs Foundation of Ministry of Education of China（No.20091101110023,20111101110012）, Beijing Municipal Natural Science Foundation（No.4102053,4101001）

Opened online:19 December 2012

Accepted by: none

Citation: Zhou Ning,Xia Yuanqing,Lu Kunfeng.Attitude Synchronization of Rigid Spacecraft Using Terminal Sliding Mode[OL]. [19 December 2012] http://en.paper.edu.cn/en_releasepaper/content/4503117

The problem of attitude synchronization and tracking for a group of rigidspacecraft is investigated in this paper under the general directedcommunication topology. Combining the strategies of finite-timecontrol, fast terminal sliding mode control and adaptivecontrol, a novel decentralized finite-time control law is proposedin the presence of inertia uncertainties and environmentaldisturbances. The new control scheme ensures that each spacecraftcan attain the desired time-varying attitude and angular velocity infinite-time while maintaining attitude synchronization with otherspacecraft in the formation. The feasibility of the controlalgorithm is investigated by an illustrative simulation example.

Keywords:Finite-time control; Attitude synchronization; Fastterminal sliding mode (FTSM); Adaptive control

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