Adaptive Finite-Time Control for Attitude Tracking of Spacecraft under Input Saturation
Publication: Journal of Aerospace Engineering
Volume 31, Issue 2
Abstract
This paper investigates two robust finite-time controllers for the attitude control of the spacecraft by using a modified terminal sliding mode surface. With the use of terminal sliding mode control and adaptive control, the controllers under input saturation can compensate both external disturbances and the uncertainty of the model parameters. By using the first and the second controller, the closed-loop system is finite-time stability and practical finite-time stability, respectively. As the system model is based on the rotation matrix, both controllers are without unwinding. Numerical simulations are given to demonstrate the effectiveness of the finite-time controllers.
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Acknowledgments
The authors acknowledge the financial support provided by the Aviation Science Foundation of China under Grant 20160153003, the Aviation Science Foundation of China under Grant 2016ZC53019 and the Fundamental Research Funds for the Central Universities (3102017OQD026).
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Published In
Journal of Aerospace Engineering
Volume 31 • Issue 2 • March 2018
Copyright
©2017 American Society of Civil Engineers.
History
Received: Apr 11, 2017
Accepted: Jul 25, 2017
Published online: Nov 22, 2017
Published in print: Mar 1, 2018
Discussion open until: Apr 22, 2018
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