Sliding Mode Control for a Nonlinear Aeroelastic System through Backstepping
Publication: Journal of Aerospace Engineering
Volume 31, Issue 1
Abstract
This paper considers an aeroelastic two-dimensional wing-flap system with uncertainty and external disturbance. Nonlinear stiffness in pitch is expressed as the second-order polynomial form. In the uncontrolled aeroelastic model, limit cycle oscillation (LCO) appears at postflutter speed. By utilizing leading-edge and trailing-edge control surfaces as the control input, a sliding mode control scheme using varying boundary layers based on backstepping design is developed to suppress aeroelastic vibration. The proposed control strategy combines the advantages of both sliding mode control with varying boundary layers and backstepping technique. In contrast to the conventional sliding mode control design, the proposed method not only avoids chattering but also obtains stronger robustness. The results of numerical simulation clearly demonstrate the effectiveness of the proposed control strategy for aeroelastic vibration suppression under saturated controller input.
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Acknowledgments
The financial support of this research by National Natural Science Foundation of China under the Grant No. 61374032 is greatly appreciated.
Disclaimer
The authors declare that there are no conflict of interests regarding the publication of this article.
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Published In
Journal of Aerospace Engineering
Volume 31 • Issue 1 • January 2018
Copyright
©2017 American Society of Civil Engineers.
History
Received: Dec 23, 2016
Accepted: May 24, 2017
Published online: Sep 20, 2017
Published in print: Jan 1, 2018
Discussion open until: Feb 20, 2018
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