Improved design methods for scarf repairs to highly strained composite aircraft structure
Improved design methods for scarf repairs to highly strained composite aircraft structure
复制标题
DOI：
10.1016/j.compstruct.2006.04.091
复制
发表时间：
2006-09
影响因子：
6.3
通讯作者：
A. Harman;Chun H. Wang
中科院分区：
文献类型：
--
作者：
A. Harman;Chun H. Wang
本文提出了一种分析方法，以优化的轮廓之间的不同模量的被粘物的嵌接接头，使胶粘剂的应力是近似均匀的沿着联合。优化的嵌接修复有望提高接头强度并减少材料去除量。有限元分析已被执行，以验证最佳的解决方案，并评估使用低刚度补丁修复碳环氧复合材料。特别是，贴片铺层对粘合应力的影响进行了研究。
This paper presents an analytical method to optimise the profile of the scarf joint between dissimilar modulus adherends so that adhesive stresses are approximately uniform along the joint. The optimised scarf repair is expected to enhance joint strength and reduce the amount of material removal. Finite element analyses have been performed to both validate the optimal solution and to evaluate the use of low stiffness patch to repair carbon epoxy composites. In particular, the influence of patch lay-up on adhesive stresses has been investigated.