分层损伤对含孔复合材料层合板剩余强度影响

肖梦丽; 张勇波; 王治华; 傅惠民; 杨鑫

doi:10.13224/j.cnki.jasp.2016.05.008

分层损伤对含孔复合材料层合板剩余强度影响

doi: 10.13224/j.cnki.jasp.2016.05.008

北京航空航天大学小样本技术研究中心, 北京 100191

基金项目:

国家自然科学基金(11501022)

北京市自然科学基金(3154034)

详细信息

作者简介:
肖梦丽(1990-),女,湖北麻城人,博士生,从事复合材料力学与失效分析研究.

中图分类号: V258;O211
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- 被引次数: 0
出版历程
- 收稿日期: 2014-08-26
- 刊出日期: 2016-05-28

Effect analysis of delamination damage on the residual strength of notched composite laminates

Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 以国产碳纤维复合材料CCF300/QY8911含孔层合板静力拉伸试验为基础,建立了符合其损伤失效模式的有限元三维预测模型.通过引入Cohesive界面单元分析了层合板拉伸过程中的分层扩展,数值模拟的结果与试验结果吻合较好,破坏载荷预测结果与试验数据相比误差在5%以内.根据CCF300复合材料构件在制造过程和实际使用中产生的孔边分层缺陷的情况,在孔边预置分层,分析了初始分层损伤对于层合板剩余强度的影响.结果表明表面预制分层对剩余强度影响较小,但会引起自由边提前分层失效.
- 复合材料层合板 /
- 渐进失效分析 /
- 分层损伤 /
- 剩余强度 /
- 有限元方法
Abstract: Based on CCF300/QY8911 notched composite laminates static tensile test, three-dimension prediction finite element model consistent with its failure mode was established. The growth of delamination in the process of tension was simulated by introducing Cohesive interface element, the simulation result had a good agreement with experimental data, the relative error of failure load between experimental data and numerical prediction was less than 5%. Given the delamination defects produced around the hole edge in the process of manufacturing and utilization of composite laminates, a prefab delamination was set near the hole for analysis, and the effect on the residual strength of laminates was investigated. The effect of embedded delamination near the surface layer on the residual strength was small, while the embedded delamination could disable delamination produced in advance near the free edge.
- composite laminates /
- progressive failure analyses /
- delamination damage /
- residual strength /
- finite element method

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参考文献(18)

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