Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer
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 clamping 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 stiffen The presented work is helpful for type selection and designing of solar powered aircraft wing panel.
Composites Dynamic response HALE Natural frequency Viscoelastic damping layer
Tiejun Liu Yong Zhang Gang Li Fenghui Wang
School of Mechanics and Civil & Architecture, Northwestern Polytechnical University, Xian 710129,Ch Sales Department of Petrochina Tarim Oilfield Company, Ku erle 841000, China School of Mechanics and Civil & Architecture, Northwestern Polytechnical University, Xian 710129,Ch
国际会议
上海
英文
491-494
2011-10-21（万方平台首次上网日期，不代表论文的发表时间）