Open Access
2014 Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite
Mingyi Huo, Xing Huo, Hamid Reza Karimi, Jianfei Ni
Abstr. Appl. Anal. 2014: 1-15 (2014). DOI: 10.1155/2014/302982


The problem of finite-time control for attitude tracking maneuver of a rigid spacecraft is investigated. External disturbance, unknown inertia parameters are addressed. As stepping stone, a sliding mode controller is designed. It requires the upper bound of the lumped uncertainty including disturbance and inertia matrix. However, this upper bound may not be easily obtained. Therefore, an adaptive sliding mode control law is then proposed to release that drawback. Adaptive technique is applied to estimate that bound. It is proved that the closed-loop attitude tracking system is finite-time stable. The tracking errors of the attitude and the angular velocity are asymptotically stabilized. Moreover, the upper bound on the lumped uncertainty can be exactly estimated in finite time. The attitude tracking performance with application of the control scheme is evaluated through a numerical example.


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Mingyi Huo. Xing Huo. Hamid Reza Karimi. Jianfei Ni. "Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite." Abstr. Appl. Anal. 2014 1 - 15, 2014.


Published: 2014
First available in Project Euclid: 2 October 2014

zbMATH: 07022120
MathSciNet: MR3176735
Digital Object Identifier: 10.1155/2014/302982

Rights: Copyright © 2014 Hindawi

Vol.2014 • 2014
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