Compressive behaviour of CFRP laminates repaired with adhesively bonded external patches
Compressive behaviour of CFRP laminates repaired with adhesively bonded external patches
复制标题
DOI：
10.1016/s0263-8223(99)00033-1
复制
发表时间：
1999-08-01
影响因子：
6.3
通讯作者：
Goutas, P
中科院分区：
文献类型：
--
作者：
Soutis, C;Duan, DM;Goutas, P
复合材料补片可用于加固和修复开裂的复合材料和金属飞机结构。用复合补片修复复合结构可以使用机械紧固，这通常会引入不期望的应力集中或粘合剂粘结、外部补片或静音补片。为了确保可靠和持久的结合，各种参数，如表面处理的质量和复合补片的设计（尺寸，形状，刚度）是非常重要的。本文介绍了粘贴外部修补的CFRP层合板在压缩载荷下的测试。据发现，关键的故障机制是纤维微屈曲在0度层片伴随着基体开裂和分层，引发的粘合剂/被粘物界面处的故障。进行三维有限元分析，以估计在修复区域的应力场。然后使用计算的应力与最大应力和平均应力失效准则来预测损伤的起始、模式和位置。精心设计的外部补片修复可以恢复80%以上的未受损抗压强度。(C)1999 Elsevier Science Ltd.保留所有权利。
Composite patches can be used to reinforce and repair both cracked composite and metallic aircraft structures. The repair of a composite structure with a composite patch may use mechanical fastening, which often introduces undesirable stress concentrations or adhesive bonding, external or hush patches. To ensure a reliable and durable bond, various parameters such as the quality of surface preparation and the design of the composite patch (size, shape, stiffness) are very important. This paper describes the testing of bonded external patch repaired CFRP laminates loaded in compression. It is found that the critical failure mechanism is fibre microbuckling in the 0 degrees plies accompanied by matrix cracking and delamination, triggered by Failures at the adhesive/adherend interface. A three-dimensional finite element analysis is performed to estimate the stress field in the repaired region. The calculated stresses are then used with the maximum stress and average stress failure criteria to predict damage initiation, mode and location. Carefully designed external patch repairs can recover more than 80% of the undamaged compressive strength. (C) 1999 Elsevier Science Ltd. All rights reserved.