Terminal Sliding Mode Control for Attitude Tracking of Spacecraft under Input Saturation
Publication: Journal of Aerospace Engineering
Volume 30, Issue 3
Abstract
This paper investigates two robust finite-time controllers for the attitude control of spacecraft based on rotation matrix. The first controller can compensate external disturbances with known bounds, whereas the second one can deal with both external disturbances and input saturation by using the hyperbolic tangent function and auxiliary system. Both controllers can avoid the singularity and converge to zero in finite time by using novel fast nonsingular terminal sliding mode control. Because the controllers are designed based on a rotation matrix that represents the set of attitudes both globally and uniquely, the system can overcome the drawbacks of unwinding. Numerical simulations are presented to demonstrate the effectiveness of the proposed control schemes.
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Acknowledgments
The authors would like to acknowledge the financial support provided by the National Natural Science Foundation of China (Grant No. 61174037), the State Key Program of National Natural Science of China (No. NSFC-61333003), CAST20120602, the Natural Science Foundation of Hunan Province, China (2015JJ6105), and the Outstanding Youth Foundation of the Education Department of Hunan Province, China (14B167).
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Published In
Journal of Aerospace Engineering
Volume 30 • Issue 3 • May 2017
Copyright
©2016 American Society of Civil Engineers.
History
Received: Apr 7, 2015
Accepted: Jul 28, 2016
Published online: Oct 27, 2016
Discussion open until: Mar 27, 2017
Published in print: May 1, 2017
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