摘要
针对碳纤维复合材料胶铆混合修理结构静载拉伸失效,对碳纤维复合材料完好板和胶铆混合修理结构进行了静载拉伸实验,分析了完好板和胶铆混合修理结构的承载能力、加载过程的应变分布特性以及两者的失效模式;通过有限元仿真分析了胶铆混合修理结构胶层和母板的损伤起始、损伤扩展;对胶铆混合修理结构不同位置的铆钉进行分区受载研究,以分析混合修理结构在拉伸载荷作用下的受力模式和传力路径,进一步揭示胶铆混合修理结构的失效模式。研究结果表明,胶铆混合修理结构在静载拉伸下,胶层首先在拉伸导致的偏心载荷引起补片翘曲所产生的剥离应力和拉伸时的横向切应力共同作用下,沿载荷方向两侧边缘开始失效并向内扩展。胶层大部分失效后,母板失效先从90°铺层外排铆钉孔边起始,沿垂直于载荷方向扩展,随后±45°铺层和0°铺层先后出现同样损伤。混合修理结构在拉伸时由胶层和铆钉共同将一部分拉伸载荷从母板传递到补片上,提升了混合修理结构的力学性能。
The experimental research was conducted on the intact composite plate and the composite bonded-rivet hybrid repairing structure,aiming at the tensile failure of carbon fiber composite bonded-rivet hybrid repairing structure.The load bearing ability and strain distribution mode during stretching and failure were analyzed.Through finite element simulation,the initiation and propagation of damage in the adhesive layer and mother board of the composite bonded-rivet hybrid re⁃pairing structure were studied.Load division research was carried out on different positions in the hybrid repairing structure to analyze its load bearing mode and load transmission route,further revealing its failure mode.The results show that un⁃der tensile load,the adhesive layer starts to fail first and expands inward along two edges of the load direction due to peel⁃ing stress caused by patch warping resulting from eccentric loading during stretching.After most of the adhesive layer fails,failure of the mother board begins from 90°layers outside row rivet holes and expands perpendicular to the load di⁃rection.Subsequently,±45°and 0°layers exhibit similar damage patterns.During stretching,part of the tensile load can be transmitted to the patch through both adhesive layer and rivets,thereby improving mechanical properties ofthe hybrid repairing structure.
作者
刘礼平
齐雨阳
蔺越国
鲍蕊
徐建新
冯振宇
卿光辉
LIU Liping;QI Yuyang;LIN Yueguo;BAO Rui;XU Jianxin;FENG Zhenyu;QING Guanghui(College of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China;School of Aeronautic Science and Engineering,Beihang University,Beijing 100083,China;College of Safety and Engineering,Civil Aviation University of China,Tianjin 300300,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2023年第24期225-238,共14页
Acta Aeronautica et Astronautica Sinica
基金
天津市科技计划(21JCYBJC00710)。
关键词
复合材料
胶铆混合修理
有限元分析
失效模式
拉伸强度
composite materials
adhesive-rivet hybrid repair
finite element analysis
failure mode
tensile strength
