Enhancing Flight Envelope for a Nonlinear Aeroelastic Wing-Section Using Adaptive Fuzzy Sliding Mode Control Law
Publication: Journal of Aerospace Engineering
Volume 35, Issue 3
Abstract
This paper presents an adaptive fuzzy sliding mode controller (AFSMC) for the control of a nonlinear aeroelastic wing section. The proposed controller estimates both the model dynamics of the system and the switching control of the sliding mode. Furthermore, the designed controller’s strategy is to enhance quality and ensure flight safety by providing additional damping to the already stable system and increasing the flight speed beyond the open-loop flutter speed. The aeroelastic system describes the plunge and pitch motions of the aircraft wing-section equipped with leading and trailing edge control surfaces. Additionally, the selected two-degree-of-freedom model includes structural stiffness nonlinearities and quasi-steady aerodynamics. The simulation results show the effectiveness of the proposed controller toward suppressing flutter and LCOs and reducing the vibrational level in the subcritical flight speed range. Additionally, the designed control strategy effectively controls and derives the state trajectories to the origin despite uncertainties and gust loads.
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Data Availability Statement
Some or all data, models, or code that support the findings of this study are available from the corresponding author on reasonable request.
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Published In
Journal of Aerospace Engineering
Volume 35 • Issue 3 • May 2022
Copyright
© 2022 American Society of Civil Engineers.
History
Received: Nov 17, 2020
Accepted: Nov 29, 2021
Published online: Jan 27, 2022
Published in print: May 1, 2022
Discussion open until: Jun 27, 2022
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