Finite-Time Attitude Control of Multiple Rigid Spacecraft}%uthorCHN{张三丰ffil{1},李四ffil{2}

Zhou Ning; Xia Yuanqing

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Finite-Time Attitude Control of Multiple Rigid Spacecraft}%uthorCHN{张三丰ffil{1},李四ffil{2}

Zhou Ning,Xia Yuanqing *

School of Automation, Beijing Institute of Technology, Beijing 100081

*Correspondence author

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Funding: Beijing Municipal Natural Science Foundation（No.4102,4101001）, the Ph.D.Programs Foundation of Ministry of Education of China （No.20091101110023,20111101110012）, the National Natural Sicence Foundation of China（No.61225015,60974011）, The workof Xia Yuanqing was supported by the National Basic Research Programof China (973 Program) （No.2012CB720000）

Opened online:28 December 2012

Accepted by: none

Citation: Zhou Ning,Xia Yuanqing.Finite-Time Attitude Control of Multiple Rigid Spacecraft}%uthorCHN{张三丰ffil{1},李四ffil{2}[OL]. [28 December 2012] http://en.paper.edu.cn/en_releasepaper/content/4503114

This paper investigates the control problem of the finite-timeattitude synchronization and tracking for a group of rigidspacecraft in the presence of environmental disturbances. A new fastterminal sliding manifold is developed for the multiple spacecraftformation flying under the undirected graph topology. Based on thefinite-time control and adaptive control strategies, a noveldecentralized finite-time control law is proposed to force thespacecraft attitude error dynamics to converge to the small regionsin finite time, and an adaptive law is applied to estimate thedisturbance. The finite-time convergence and stability of the closedloop system can be guaranteed by Lyapunov theory. Simulationexamples are provided to illustrate the feasibility of the controlalgorithm.

Keywords:Attitude synchronization; Fast terminal sliding manifold (FTSM); Finite-time control; Adaptive control

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