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Computational fluid dynamics-based transonic flutter suppression with control delay

Computational fluid dynamics-based transonic flutter suppression with control delay
Computational fluid dynamics-based transonic flutter suppression with control delay
This work investigates the effects of control input time delay on closed-loop transonic computational aeroelastic analysis. Control input time delays are becoming critical as the demand for high frequency control actions is increasing. The flow in transonic conditions exhibits strong nonlinearities which require accurate physical modeling techniques, in turn resulting in large dimensional systems that are computationally costly to solve. A unified framework is demonstrated for the robust and efficient generation of reduced order models. Once generated, the reduced order model is employed for the flutter boundary search, and excellent agreement with the large order coupled model is demonstrated. The aero-servo-elastic reduced order model is then exploited to design a feedback control law, which is implemented in the fully coupled computational fluid/structural dynamics solver. As expected, the controller effectiveness is found to degrade for increasing time delay, up to a critical value where the controller fails to suppress flutter. It is shown that a controller for a time-delay system may be designed using the same aero-servo-elastic reduced order model, incurring in no extra costs or complications. The new controller is found to achieve excellent flutter suppression characteristics. The aero-servo-elastic reduced order model may also be used to identify, for a given feedback controller, the critical value of control input time delay at which the closed-loop aero-servo-elastic system loses its stability. The test cases are for a two-dimensional pitch-plunge aerofoil section and the AGARD 445.6 wing modified with a trailing-edge control surface.
0889-9746
183-206
Zhou, Qiang
419faeb8-bdca-47ab-9aec-ce2bd7a15e22
Li, Dong-feng
dd8d9d17-ac74-4d9c-aa30-13817bb4c466
Da Ronch, Andrea
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Chen, Gang
83a5c46f-13cc-4be3-ad5b-698a69e82b8e
Li, Yue-ming
f52843d0-0f3f-440e-810c-8ae25ef32ffd
Zhou, Qiang
419faeb8-bdca-47ab-9aec-ce2bd7a15e22
Li, Dong-feng
dd8d9d17-ac74-4d9c-aa30-13817bb4c466
Da Ronch, Andrea
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Chen, Gang
83a5c46f-13cc-4be3-ad5b-698a69e82b8e
Li, Yue-ming
f52843d0-0f3f-440e-810c-8ae25ef32ffd

Zhou, Qiang, Li, Dong-feng, Da Ronch, Andrea, Chen, Gang and Li, Yue-ming (2016) Computational fluid dynamics-based transonic flutter suppression with control delay. Journal of Fluids and Structures, 66, 183-206. (doi:10.1016/j.jfluidstructs.2016.07.002).

Record type: Article

Abstract

This work investigates the effects of control input time delay on closed-loop transonic computational aeroelastic analysis. Control input time delays are becoming critical as the demand for high frequency control actions is increasing. The flow in transonic conditions exhibits strong nonlinearities which require accurate physical modeling techniques, in turn resulting in large dimensional systems that are computationally costly to solve. A unified framework is demonstrated for the robust and efficient generation of reduced order models. Once generated, the reduced order model is employed for the flutter boundary search, and excellent agreement with the large order coupled model is demonstrated. The aero-servo-elastic reduced order model is then exploited to design a feedback control law, which is implemented in the fully coupled computational fluid/structural dynamics solver. As expected, the controller effectiveness is found to degrade for increasing time delay, up to a critical value where the controller fails to suppress flutter. It is shown that a controller for a time-delay system may be designed using the same aero-servo-elastic reduced order model, incurring in no extra costs or complications. The new controller is found to achieve excellent flutter suppression characteristics. The aero-servo-elastic reduced order model may also be used to identify, for a given feedback controller, the critical value of control input time delay at which the closed-loop aero-servo-elastic system loses its stability. The test cases are for a two-dimensional pitch-plunge aerofoil section and the AGARD 445.6 wing modified with a trailing-edge control surface.

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Computational Fluid Dynamics-based Transonic Flutter Suppression with Control Delay To be published in.pdf - Accepted Manuscript
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Accepted/In Press date: 4 July 2016
e-pub ahead of print date: 11 August 2016
Published date: October 2016
Organisations: Faculty of Engineering and the Environment

Identifiers

Local EPrints ID: 397756
URI: http://eprints.soton.ac.uk/id/eprint/397756
ISSN: 0889-9746
PURE UUID: b474e42c-4607-4861-87f9-b504dd91e3bb

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Date deposited: 06 Jul 2016 09:15
Last modified: 07 Oct 2020 06:03

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Contributors

Author: Qiang Zhou
Author: Dong-feng Li
Author: Andrea Da Ronch
Author: Gang Chen
Author: Yue-ming Li

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