Attitude stabilization of rigid spacecraft with finite-time convergence

The problem of attitude control for a spacecraft model which is nonlinear in dynamics with inertia uncertainty and external disturbance is investigated in this paper. Two sliding mode controllers are proposed to force the state variables of the closed‐loop system to converge to the origin in finite...

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Bibliographic Details
Published inInternational journal of robust and nonlinear control Vol. 21; no. 6; pp. 686 - 702
Main Authors Zhu, Zheng, Xia, Yuanqing, Fu, Mengyin
Format Journal Article
LanguageEnglish
Published Chichester, UK John Wiley & Sons, Ltd 01.04.2011
Subjects
adaptive control
attitude stabilization
Controllers
Disturbances
Dynamical systems
finite-time stability
Mathematical models
Nonlinear dynamics
Nonlinearity
sliding mode control
Uncertainty
Vibration
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Summary:The problem of attitude control for a spacecraft model which is nonlinear in dynamics with inertia uncertainty and external disturbance is investigated in this paper. Two sliding mode controllers are proposed to force the state variables of the closed‐loop system to converge to the origin in finite time. Specially, the second control design consists of the estimation of the uncertainty and disturbance by adaptive method and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies. Copyright © 2010 John Wiley & Sons, Ltd.
Bibliography:istex:0CFFF862398F53376F750F3C5C4776001E37E4CC
ArticleID:RNC1624
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ObjectType-Article-2
SourceType-Scholarly Journals-1
ObjectType-Feature-1
content type line 23
ISSN:1049-8923
1099-1239
1099-1239
DOI:10.1002/rnc.1624