复合材料层合板机械连接结构累积损伤模型和挤压性能试验研究

张爽; 王栋; 郦正能; 寇长河; 章怡宁

复合材料层合板机械连接结构累积损伤模型和挤压性能试验研究

1.
北京航空航天大学飞机设计研究所, 北京 100083 ;

基金项目: 凡舟基金资助项目(20050503)

详细信息

通讯作者:
郦正能, 教授, 主要从事飞机结构设计、复合材料力学性能等方面的研究　E-mail : zjk @ase. buaa. edu. cn

中图分类号: TB330.1
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出版历程
- 收稿日期: 2005-05-25
- 修回日期: 2005-08-08
- 刊出日期: 2006-04-14

Numerical calculation of damage accumulation and bearing strengthexperimental verif ication for composite single bolted joint

1.
Aircraf t Design and Research Institute| Beijing University of Aeronautics and Ast ronautics|Beijing 100083| China ;

摘要

摘要: 建立了三维累积损伤有限元模型, 采用扩展拉格朗日乘子法对螺栓表面和复合材料层合板孔壁间的接触行为进行了模拟。对复合材料层合板中纤维断裂、基体开裂和纤维2基体剪切3 类基本损伤类型的产生、扩展以及它们之间的关联性进行了研究。计算得到了复合材料层合板单钉连接结构的载荷2位移曲线, 预测了它们的初始挤压破坏载荷。同时, 进行了T300 帘子布/ Q Y8911 双马来酰亚胺树脂层合板单钉单搭螺栓挤压强度试验,验证了不同铺层类型和结构尺寸对复合材料层合板机械连接挤压性能的影响。试验结果和计算结果吻合较好, 证明了该模型和算法的有效性。
- 层合板 /
- 机械连接 /
- 累积损伤 /
- 接触模型
Abstract: A three-dimensional non-linear progressive damage model was developed to predict the response of composite laminates with a single bolt . The analysis took into account the contact at the bolt-hole interface by Augmented Lagrangian Contact Algorithm. The objectives of the study were to investigate the onset and development of thefibre damage , mat rix damage , fibre-mat rix shear , and their relationship. From the load-displacement curves drawnfrom the calculation , the initial bearing damage strength was predicted. The effect s of stacking sequences and geomet rical parameters on the bearing st rength were determined experimentally. Good agreement between experimentalresult s and numerical predictions is observed.
- composite laminates /
- single bolt /
- progressive damage /
- contact model