北京航空航天大学学报 ›› 2014, Vol. 40 ›› Issue (12): 1786-1792.doi: 10.13700/j.bh.1001-5965.2014.0010

• 论文 • 上一篇    

复合材料单搭接胶接接头试验研究与数值模拟

梁祖典1, 燕瑛1, 张涛涛1, 李剑峰1, 孟祥吉1, 廖宝华2   

  1. 1. 北京航空航天大学 航空科学与工程学院, 北京 100191;
    2. 成都飞机设计研究所, 成都 610041
  • 收稿日期:2014-01-13 出版日期:2014-12-20 发布日期:2014-12-30
  • 作者简介:梁祖典(1988-),男,山东平度人,硕士生,liangzudian@163.com.
  • 基金资助:

    国家973计划资助项目(2011CB606105)

Experimental investigation and numerical simulation of composite laminate adhesively bonded single-lap joints

Liang Zudian1, Yan Ying1, Zhang Taotao1, Li Jianfeng1, Meng Xiangji1, Liao Baohua2   

  1. 1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. Chengdu Aircraft Design and Research Institute, Chengdu 610041, China
  • Received:2014-01-13 Online:2014-12-20 Published:2014-12-30

摘要:

针对不同搭接长度和不同被胶接件厚度的T300/QY8911层合板单搭接胶接接头进行了试验研究和数值模拟.建立了不同试验参数下的三维有限元模型,基于Hashin准则和连续介质损伤力学(CDM,Continuum Damage Mechanics)预测层合板面内损伤的起始和演化,应用黏聚区模型(CZM,Cohesive Zone Model)模拟层合板的分层损伤及胶层的失效.系统地研究了接头在不同参数下的失效模式、破坏形貌和极限载荷等的变化,模拟结果与试验吻合良好,验证了有限元分析模型的有效性.通过对接头的破坏形貌和应力分布进一步分析发现,胶接连接的失效模式和极限载荷均与胶接长度和被胶接件厚度有关;模拟接头胶接区在不同加载时刻的应力分布变化,反映了胶接连接在拉伸载荷下的破坏起始和演化过程.

关键词: 复合材料层合板, 单面搭接, 渐进损伤, 黏聚区模型, 失效模式, 应力分析

Abstract:

Both experimental tests and finite element method (FEM) simulation were implemented to investigate T300/QY8911 composite laminate single-lap joints with various single-lap length and adherend thickness. 3D finite element models of the joints under various experimental parameters were established. The damage initiation and progressive damage evolution of laminates were predicted based on Hashin criterion and continuum damage mechanics (CDM). The delamination of laminates and the failure of adhesive were simulated by cohesive zone model (CZM). The change of failure modes, damage contours and ultimate-loads of adhesively bonded single-lap joints were investigated systematically under various parameters. The FEM simulation accords well with experimental results which proves the efficiency of FEM simulation. Damage contours and stress distribution of the joints show that the failure modes and ultimate-loads of single-lap joints are both related to the single-lap length and adherend thickness. Simulation of the stress distribution of joints at different loading points reflects damage initiation and evolution of adhesively bonded single-lap joints under extension loads.

Key words: composite laminates, single-lap joints, progressive damage, cohesive zone models, failure modes, stress analysis

中图分类号: 


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