Adaptive Control for Spacecraft Rendezvous Subject to Time-Varying Inertial Parameters and Actuator Faults
Publication: Journal of Aerospace Engineering
Volume 32, Issue 5
Abstract
A novel adaptive fault-tolerant control strategy is proposed for a spacecraft rendezvous maneuver. The six-degree-of-freedom (6-DOF) nonlinear model is expressed in the pursuer’s body frame, which consists of relative attitude and orbit dynamics in the presence of unknown time-varying inertia parameters, bounded disturbances, and actuator faults. A continuous adaptive control strategy is developed for the pursuer where a modification term and projection algorithm are employed in the adaptation laws to ensure the estimates of the unknown parameters remain positive and bounded. It is proven that the proposed strategy ensures the ultimate boundedness of all the signals in the closed-loop system and the asymptotic stability of the relative dynamics. Numerical simulations verify the effectiveness of the proposed control strategy.
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Acknowledgments
This work was supported by the Korea Astronomy and Space Science Institute (KASI) and Yonsei Research Collaboration Program for the Frontiers of Astronomy and Space Science. This work was also supported by the Space Basic Technology Development Program through the National Research Foundation of Korea funded by the Ministry of Science and ICT of Republic of Korea (2018MIA3A3A02065610).
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Published In
Journal of Aerospace Engineering
Volume 32 • Issue 5 • September 2019
Copyright
©2019 American Society of Civil Engineers.
History
Received: Sep 6, 2018
Accepted: Feb 1, 2019
Published online: May 31, 2019
Published in print: Sep 1, 2019
Discussion open until: Oct 31, 2019
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