含孔复合材料层合板温度环境下的拉伸性能

翁晶萌; 温卫东; 徐颖; 赵杨

doi:10.13224/j.cnki.jasp.2015.05.018

含孔复合材料层合板温度环境下的拉伸性能

doi: 10.13224/j.cnki.jasp.2015.05.018

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016

基金项目:

中央高校基本科研业务费科研专项资金(NZ2012103)

详细信息

作者简介:
翁晶萌(1989-),女,陕西渭南人,博士生,主要从事先进复合材料与结构设计技术研究.

中图分类号: V231
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出版历程
- 收稿日期: 2013-11-27
- 刊出日期: 2015-05-28

Tensile properties of laminated composites with a hole under temperature conditions

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 根据增量形式的虚功原理和单层板理论,推导了基于温度环境下复合材料层合板的应力分析公式,结合逐渐损伤分析理论,建立了考虑温度影响的复合材料层合板的逐渐损伤强度分析方法.在此基础上,对含孔复合材料层合板在22,80,120℃下的拉伸失效过程进行预测,与80℃和120℃下的试验结果相比,预测强度值的最大误差为-2.28%.研究表明:随着温度的升高,含孔复合材料层合板的初始纤维损伤强度和破坏强度逐渐降低,而其初始基体损伤强度逐渐增大.
- 温度环境 /
- 复合材料层合板 /
- 热应力 /
- 逐渐损伤 /
- 强度
Abstract: The stress analysis equations of laminated composites under temperature conditions was derived based on the virtual work principle of incremental form and the theory of unidirectional ply, and the progressive damage stress analysis method of laminated composites considering the effect of temperature was established by integrating the progressive damage analysis theory. On this basis, the tensile damage processes of laminated composites with a hole at 22, 80, 120℃ were predicted; compared with experimental results at 80℃ and 120℃, the maximum error of predicted strength was -2.28%. Research shows that the initial fiber damage strength and the failure strength of laminated composites with a hole are reduced with temperature rising, while the initial matrix damage strength rises gradually.
- temperature conditions /
- laminated composites /
- thermal stress /
- progressive damage /
- strength

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参考文献(18)

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