含裂纹铆钉搭接板的权函数法与扩展寿命分析  

Weight function approach and crack growth life analysis of rivet lap panels

作　　者：任彦伸 饶聃钰 徐武[1] REN Yanshen;RAO Danyu;XU Wu(School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240 China;Commercial Aircraft Corporation of China Ltd.,Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海交通大学航空航天学院,上海200240 [2]中国商用飞机责任有限公司上海飞机设计研究院,上海201210

出　　处：《哈尔滨工业大学学报》2024年第4期53-60,共8页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金(12172217)。

摘　　要：铆钉搭接结构是典型的多位置损伤敏感结构,容易在多个铆钉孔边萌生疲劳裂纹,进而威胁飞机结构安全。由于裂纹个数、位置和大小随机多变,铆钉与平板间存在复杂的接触关系。为高效、准确计算多铆钉搭接板的应力强度因子以进行裂纹扩展寿命分析,提出针对搭接结构复杂裂纹问题的权函数分析方法。首先,对多铆钉搭接板的复杂裂纹构型进行合理简化分类,利用其对应的权函数求解应力强度因子。然后,采用有限元分析计算含裂纹多铆钉搭接板的应力强度因子以验证权函数法的计算精度。最后,将经验证的权函数分析方法结合Paris裂纹扩展公式,对铆钉搭接结构进行疲劳裂纹扩展分析,并通过试验验证分析方法的有效性。结果表明,采用权函数法计算的应力强度因子与完全采用有限元方法计算的应力强度因子的相对差别小于5%,分析预测的裂纹扩展寿命与试验结果吻合良好,且计算效率比完全采用有限元法快3个数量级,进而为铆钉连接结构孔边裂纹的应力强度因子和疲劳裂纹扩展分析提供了一个有效方法。Rivet lap joint is a typical structure susceptible to multi-site damage,which is prone to initiate rivet holes-edge crack.It significantly threatens the safety of aircraft structures.Due to the randomness of the crack number,position,size,there exists a complex contact relationship between rivets and plates.In order to efficiently and accurately calculate the stress intensity factor of multi rivet lap joint structures for crack propagation life analysis,a weight function analysis method for rivet lap joint structure is proposed to address the complex crack issues in lap joint structures.Firstly,the crack configurations of rivet lap joint structures are reasonably simplified and classified,the corresponding weight functions are used to calculate the stress intensity factors of different crack configurations.Then,finite element analysis is conducted to compute the stress intensity factor to validate the accuracy of the weight function method.Finally,combined with the Paris crack growth formula,fatigue crack growth of the rivet lap joint structures are predicted,and the effectiveness of the present method is verified by experiments.The results show that the relative difference between the stress intensity factor calculated by the weight function method and the finite element method is less than 5%.The predicted crack growth life is in good agreement with the test results,and the computational efficiency is three orders of magnitude faster than that of the finite element method.This paper provides an effective method for the stress intensity factor and fatigue crack growth analyses of rivet lap joint structures.

关 键 词：权函数法 铆钉连接结构 疲劳裂纹扩展 应力强度因子 有限元分析 

分 类 号：V215.6[航空宇航科学与技术—航空宇航推进理论与工程]