碳纤维增强树脂基复合材料层合板胶螺混合连接失效机制  

Failure mechanism of carbon fiber reinforced polymer bonded-bolted hybrid connection

作　　者：刘礼平[1] 段科好 徐卓 冯振宇 蔺越国[1] 郑亦媚 宋肖肖 LIU Liping;DUAN Kehao;XU Zhuo;FENG Zhenyu;LIN Yueguo;ZHENG Yimei;SONG Xiaoxiao(College of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China;College of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China;Sino-European Institute of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300 [2]中国民航大学安全科学与工程学院,天津300300 [3]中国民航大学中欧航空工程师学院,天津300300

出　　处：《复合材料学报》2023年第1期590-600,共11页Acta Materiae Compositae Sinica

基　　金：中央高校科研基本业务费(3122018D040)。

摘　　要：为研究碳纤维增强树脂基复合材料(CFRP)层合板单搭接双螺栓胶螺混合连接失效机制,采用基于断裂能断裂准则的连续渐进退化方式,仿真CFRP层合板刚度退化,采用基于能量的B-K准则仿真胶层的损伤演化,建立胶螺混合连接结构渐进损伤三维有限元模型,有限元模型预测的最大失效载荷与实验结果吻合较好。搭接长度L_(a)为影响胶螺混合接头刚度和强度的重要几何参数,螺栓的位置不会明显影响接头的刚度,粘结面积越大,强度越大。胶螺混合接头在拉伸载荷作用下,由于二次弯曲效应的影响,螺栓向左倾斜,搭接区域的胶层损伤起始于搭接区域胶层外侧,并由外侧向内部扩展到钉孔附近,当胶层损伤扩展到钉孔附近时,螺栓承载增加,胶层和螺栓共同承载,此时CFRP层合板开始出现损伤;最终,左侧钉孔处的上层合板和右侧钉孔处的下层合板产生分层损伤并发生断裂。In order to study the failure mechanism of the single-lap two-bolt bonded-bolted hybrid connection of carbon fiber reinforced polymer(CFRP)laminates,the continuous progressive degradation method based on fracture energy fracture criterion was used to simulate the stiffness degradation of CFRP laminates,and the B-K criterion based on energy was used to simulate the damage evolution of the adhesive layer.A three-dimensional finite element model of progressive damage of the bonded-bolted hybrid connection structure was established.The maximum failure load predicted by the finite element model is in good agreement with the experimental results.Lap length L_(a) is an important geometric parameter affecting the stiffness and strength of the bonded-bolted hybrid joint.The position of bolt will not significantly affect the stiffness of joint.The larger the bonding area,the greater the strength.Under the action of tensile load,the bolt of the bonded-bolted hybrid joint is inclined to the left due to the influence of the secondary bending effect.The adhesive layer damage in the overlap area starts from the outside of the adhesive layer in the overlap area and expands from the outside to the inside to the vicinity of the bolt hole.When the damage of the adhesive layer extends to the vicinity of the bolt hole,the load of the bolt increases,and the adhesive layer and the bolt bear the load together.At this time,the CFRP laminates begin to damage,and the upper composite plate at the left hole and the lower composite plate at the right hole produce delamination damage and fracture.

关 键 词：碳纤维增强树脂基复合材料(CFRP) 胶螺混合连接 失效机制 有限元分析 二次弯曲效应 

分 类 号：V260[航空宇航科学与技术—航空宇航制造工程]