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Nonlinear Aeroelastic Panel Flutter Based on Proper Orthogonal Decomposition

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Abstract:

It is commonly accepted that 36 in vacuo natural modes (NMS) are needed for converged, limit-cycle oscillations (LCOs) of isotropic or laminated anisotropic rectangular panels in supersonic air flow. It’s computationally costly for nonlinear aeroelastic panel response using such a large number of modes, and it also causes complexity and difficultly in designing controllers for panel flutter suppression. Based on Hamilton principle, the aeroelastic finite element motion equations of the 3-D panel are established by using the von Karman large deflection theory, first-order piston theory aerodynamics, the proper orthogonal decomposition (POD) method are adopted to construct a reduced order model of the panel, then the reduced panel flutter equations are solved in time domain using a numerical integration method. Comparing with the LCOs calculated by using 36NMS, the results obtained by using the reduced order model based on POD method (POD/ROM) show a good agreement.

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Periodical:

Applied Mechanics and Materials (Volume 482)

Pages:

42-48

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.482.42

Citation:

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Online since:

December 2013

Authors:

Jian Zhou*, Zhi Chun Yang

Keywords:

LCO, Nonlinear Aeroelasticity, Panel Flutter, Proper Orthogonal Decomposition (POD)

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© 2014 Trans Tech Publications Ltd. All Rights Reserved

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