Attitude Coordination Control for Formation Flying Spacecraft Based on the Rotation Matrix
Publication: Journal of Aerospace Engineering
Volume 30, Issue 5
Abstract
Two attitude coordination controllers that make the system converge to the equilibrium point in finite time are designed for spacecraft formation flying with actuator saturation constraints. The first finite-time attitude coordination controller is suitable for the situation that all states of the closed-loop system are available. To deal with the problem of failing to measure angular velocity, a novel filter is presented in the second finite-time attitude coordination controller. Because the model of spacecraft formation flying is established based on the rotation matrix, the closed-loop system does not have the drawback of unwinding. The theoretical analysis and simulation results are given to prove the validity of the proposed controllers.
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Acknowledgments
The authors acknowledge the financial support provided by the Aviation Science Foundation of China under Grants 20160153003 and 2016ZC53019.
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Published In
Journal of Aerospace Engineering
Volume 30 • Issue 5 • September 2017
Copyright
©2017 American Society of Civil Engineers.
History
Received: Sep 30, 2016
Accepted: Mar 2, 2017
Published online: Jun 6, 2017
Published in print: Sep 1, 2017
Discussion open until: Nov 6, 2017
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