Wing Flutter Suppression under the Influence of Fuel Sloshing in External Tank
Publication: Journal of Aerospace Engineering
Volume 34, Issue 5
Abstract
The control of aeroelastic response of a wing section with influence of the fuel sloshing in external tank is examined through analytical studies. Based on the simplified mass-spring-damper equivalent mechanical model of the liquid sloshing and the dynamic modeling method of the wing/store system, the aeroelastic model of the two-dimensional wing/external tank/fuel sloshing system is established in this paper. The aeroelastic instability of the system is studied, and a flutter suppression controller is designed based on linear active disturbance rejection control (LADRC). The stability analysis shows that the tracking error and the estimation error of the linear state observer (ESO) are convergent. It is shown through simulation results that wing flutter suppression under the interference of fuel sloshing and external tank vibrating can be achieved by using two control surfaces.
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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 upon reasonable request.
Acknowledgments
This work was supported by the Fundamental Research Funds for the Central Universities (No. 3072020CFT0203) and Key Laboratory of dual medium power technology in Hebei Province (HG36803; HG36806; HG36807).
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Published In
Journal of Aerospace Engineering
Volume 34 • Issue 5 • September 2021
Copyright
© 2021 American Society of Civil Engineers.
History
Received: Jul 24, 2020
Accepted: Dec 23, 2020
Published online: Jun 18, 2021
Published in print: Sep 1, 2021
Discussion open until: Nov 18, 2021
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