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Abstract and Applied Analysis
Volume 2014 (2014), Article ID 302982, 15 pages
Research Article

Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite

1Department of Control Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
2College of Engineering, Bohai University, Jinzhou 121000, China
3Department of Engineering, Faculty of Engineering and Science, The University of Agder, 4898 Grimstad, Norway

Received 7 November 2013; Accepted 8 January 2014; Published 26 February 2014

Academic Editor: Junmin Wang

Copyright © 2014 Mingyi Huo et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


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.