含分层损伤复合材料层合板振动特性

漆文凯; 程博; 刘磊

含分层损伤复合材料层合板振动特性

南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2012-05-11
- 刊出日期: 2013-04-28

Vibration characteristic of composite laminates with delamination

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 针对复合材料层合板分层损伤区域上、下子板的畸变模态,采用自定义矩阵单元模拟其损伤区的接触刚度,建立了一种合理的层合板分层损伤有限元振动分析模型;在此基础上研究了分层深度和分层大小对复合材料层合板振动特性的影响.数值模拟结果与实验结果的对比表明:采用的自定义矩阵单元可以有效地模拟层合板的分层损伤,模态计算值与实验值的最大误差为10.67%,最小误差为0.34%;分层深度和分层大小对复合材料层合板振动特性有较大影响,随分层深度变化,固有频率最多下降50%;随分层大小变化,前4阶固有频率最多下降12%.
- 复合材料层合板 /
- 分层损伤 /
- 自定义矩阵单元 /
- 有限元法 /
- 振动特性
Abstract: A reasonable finite element model was established to simulate composite laminates with delamination by using the user-defined matrix element to simulate contacting element in delamination region for distortion mode of the upper and lower sublaminates,and the selection of connection stiffness values was studied as well.This article focuses on the vibration performance of composite laminates with delamination depth and delamination size.The comparison of numerical simulation and experimental results indicates that it is feasible to simulate the delamination of composite laminates with the user-defined matrix elements; the maximum error of the modal calculation and the experimental values is 10.67%, and the minimum error is 0.34%; delamination depth and size have significant effects on vibration characteristic of composite laminates, and the natural frequency of laminates declines up to 50% with change of delamination depth; the first to fourth order natural frequencies of laminates decrease up to 12% with change of delamination size.
- composite laminates /
- delamination /
- user-defined matrix elements /
- finite element method /
- vibration characteristic

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参考文献(16)

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