Spacecraft Attitude Fault Tolerant Control with Terminal Sliding-Mode Observer
Publication: Journal of Aerospace Engineering
Volume 28, Issue 1
Abstract
A velocity-free attitude fault tolerant control scheme is presented to stabilize spacecraft attitude. A terminal sliding-mode observer is developed to reconstruct system states. With the reconstructed attitude and angular velocity, a control law is synthesized without any knowledge on actuator faults. The controller guarantees all the signals of the closed-loop attitude system to be uniformly ultimately bounded even in the presence of actuator fault and external disturbance. The control power is rigorously ensured to be within the maximum magnitude of output torque. An illustrative example is presented to evaluate the control performance.
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Acknowledgments
This present work was supported by the National Natural Science Foundation of China (61004072, 61273175); Program for New Century Excellent Talents in University (NCET-11-0801); Heilongjiang Province Science Foundation for Youths (QC2012C024); and the Fundamental Research Funds for the Central Universities (HIT.NSRIF.2009003, HIT.BRETIII.201212). The authors would also like to thank the editors and reviewers for their very constructive comments and suggestions, which have greatly help improve the quality and presentation of the paper.
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Published In
Journal of Aerospace Engineering
Volume 28 • Issue 1 • January 2015
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Sep 27, 2012
Accepted: Jan 7, 2013
Published online: Jan 9, 2013
Discussion open until: Nov 19, 2014
Published in print: Jan 1, 2015
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