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Synthesis of an active flutter suppression system in the transonic domain using a computational model

Published online by Cambridge University Press:  20 May 2021

R. Vepa Open the ORCID record for R. Vepa [Opens in a new window]  and
J.R. Kwon
R. Vepa*
Affiliation:
School of Engineering and Material Science Queen Mary University of LondonLondonE14NSUK
J.R. Kwon
Affiliation:
Aerospace Technology Research Institute Agency for Defense Development Daejeon, 34186Republic of Korea
*
r.vepa@qmul.ac.uk
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Abstract

Control laws for implementing active flutter suppression are generally derived from linear aeroelastic models. In this paper, families of control laws for implementing an active flutter suppression system were initially designed using linearised aeroelastic models based on the doublet lattice method after ignoring the aerodynamic loads associated with relatively faster time scales. Using these preliminary sets of control laws and the nonlinear transonic small disturbance theory, near-optimum control laws were chosen in the transonic domain to maximally increase the flutter speed of a typical aircraft wing by at least 16% or more. Thus it is shown that it is feasible to systematically design near-optimal control laws for active flutter suppression using computational models in transonic flow. The doublet lattice method coupled with the zeroth-order matrix Padé approximant provided the fastest method for synthesising a large number of preliminary control laws. The methodology was successfully demonstrated by applying it to two benchmarking examples.

Keywords

Unsteady transonic flowPotential flowTransonic small disturbanceDoublet lattice methodFlutter analysisActive flutter suppressionControl law synthesis
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1293 , November 2021 , pp. 2002 - 2020
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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