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

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
Chapter
Chapter 2: Dynamics
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, Y. Zhang, G. Li, F. H. Wang, "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
$32.00
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