Multivariable Disturbance Observer–Based Fuzzy Fast Terminal Sliding Mode Attitude Control for a Hypersonic Vehicle
Publication: Journal of Aerospace Engineering
Volume 32, Issue 2
Abstract
This paper develops a comprehensive methodology to address the attitude control problem of hypersonic vehicles in the presence of matched model uncertainties and external disturbances. Initially, a nonlinear dynamic model was established dedicated to attitude control. Afterward, a multivariable disturbance observer was constructed to estimate the lumped disturbance for compensation. Moreover, the dynamic inversion technique was adopted to cancel the nonlinear dynamics for decreasing complexity of controller design. To proceed, a novel fuzzy fast terminal sliding mode control strategy was designed to achieve a significant performance of attitude command tracking with the integrated consideration of robustness, chattering alleviation, and actuator saturation rejection. The finite-time stability of the closed-loop system was proven by means of the finite-time bounded function method and the Lyapunov theory. Simulation results demonstrated that the proposed synthetic scheme showed preferable performance and strong robustness in view of attitude command tracking.
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Acknowledgments
This work was supported in part by the National Natural Science Foundation of China (Grant Nos. 61174221 and 61402039). The authors greatly acknowledge their information and financial support. The authors sincerely appreciate the editor and all the anonymous reviewers who improved the quality of this paper.
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Information
Published In
Journal of Aerospace Engineering
Volume 32 • Issue 2 • March 2019
Copyright
©2018 American Society of Civil Engineers.
History
Received: Jan 13, 2018
Accepted: Sep 7, 2018
Published online: Dec 24, 2018
Published in print: Mar 1, 2019
Discussion open until: May 24, 2019
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