Novel Adaptive Saturated Attitude Tracking Control of Rigid Spacecraft with Guaranteed Transient and Steady-State Performance
Publication: Journal of Aerospace Engineering
Volume 31, Issue 5
Abstract
In this paper, a novel adaptive model-free attitude tracking control method is investigated for rigid spacecraft with consideration of the external disturbance, unknown inertia matrix, and input saturation. First, the considered attitude tracking system with input saturation is transformed into a Lagrangian model, and a dead zone–based model is used to describe the saturation nonlinearity. Second, using the prescribed performance control theory, a static prescribed performance attitude control scheme is presented, by which the transient and steady-state performance (including the convergence rate, overshoot, and boundedness) of the attitude tracking system is proved to be guaranteed. Third, in order to improve the performance of the static prescribed performance control scheme, a novel learning-based supplementary control scheme is presented based on the approximate dynamic programming. Finally, two groups of numerical simulations are used to illustrate the effectiveness of the proposed learning-based prescribed performance attitude control method.
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Acknowledgments
The authors would like to extend thanks for the support of the Major Program of the National Natural Science Foundation of China (Grant Nos. 61690210 and 61690211) and the sponsorship by the Innovation Foundation for Doctoral Dissertations of Northwestern Polytechnical University (Grant No. CX201711).
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Published In
Journal of Aerospace Engineering
Volume 31 • Issue 5 • September 2018
Copyright
©2018 American Society of Civil Engineers.
History
Received: Nov 2, 2017
Accepted: Mar 1, 2018
Published online: Jun 13, 2018
Published in print: Sep 1, 2018
Discussion open until: Nov 13, 2018
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