Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix

Two finite-time controllers without unwinding for the attitude tracking control of the spacecraft are investigated based on the rotation matrix, in which a novel modified nonsingular fast terminal sliding manifold is developed to keep tr(R~)≠-1. The first terminal sliding mode controller can compens...

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Bibliographic Details
Published inMathematical problems in engineering Vol. 2015; no. 2015; pp. 1 - 9
Main Authors Guo, Yong, Li, Xue-Hui, Song, Shenmin
Format Journal Article
LanguageEnglish
Published Cairo, Egypt Hindawi Publishing Corporation 01.01.2015
Hindawi Limited
Subjects
Adaptive control
Closed loop systems
Control methods
Control theory
Controllers
Disturbances
Equilibrium
Mathematical analysis
Mathematical models
Rotation
Sliding mode
Sliding mode control
Spacecraft
Spacecraft attitude control
Spacecraft tracking
Terminals
Tracking
Tracking control
Vibration
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Summary:Two finite-time controllers without unwinding for the attitude tracking control of the spacecraft are investigated based on the rotation matrix, in which a novel modified nonsingular fast terminal sliding manifold is developed to keep tr(R~)≠-1. The first terminal sliding mode controller can compensate external disturbances with known bounds, while the second one can compensate external disturbances with unknown bounds by using an adaptive control method. Since the first terminal sliding mode controller is continuous, it is able to avoid chattering phenomenon. Theoretical analysis shows that both the two controllers can make spacecraft follow a time-varying reference attitude signal in finite time. Numerical simulations also demonstrate that the proposed control schemes are effective.
Bibliography:ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
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ISSN:1024-123X
1563-5147
DOI:10.1155/2015/187924