Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer

Abstract:

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In design of solar powered aircraft wing panel, vibration properties of wing panel should be considered, especially for the peak value of dynamic response. In this research, a viscoelastic damping layer is built for vibration isolation, wing panel finite element models of stiffened and no-stiffened structures base on fiber-reinforced laminates with damping layer in the middle are built. Natural frequency and displacement response are analyzed with different thickness of damping layer and structures. Result shows natural frequencies decrease as thickness increased, and that of laminates are lower than stiffened structure. The maximum displacement response value decreased when thickness increased and that of laminates is higher than structured with stiffer. The presented work is helpful for type selection and designing of solar powered aircraft wing panel.

Info:

Periodical:

Edited by:

Paul P. Lin and Chunliang Zhang

Pages:

491-494

DOI:

10.4028/www.scientific.net/AMM.105-107.491

Citation:

T. J. Liu et al., "Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer", Applied Mechanics and Materials, Vols. 105-107, pp. 491-494, 2012

Online since:

September 2011

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Price:

$35.00

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