复材双搭胶接结构应力分析与试验研究  

Stress Analysis and Experimental Study on Double-bonded Joints in Composite Structures

作　　者：邵金涛 周晚林[1] 李鹏 仇晓今 朱苏纬 SHAO Jintao;ZHOU Wanlin;LI Peng;QIU Xiaojin;ZHU Suwei(College of Mechanical and Electrical Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Public Administration,Nanjing University of Finance&Economics,Nanjing 210023,China)

机构地区：[1]南京航空航天大学机电学院,江苏南京210016 [2]南京财经大学公共管理学院,江苏南京210023

出　　处：《机械制造与自动化》2020年第4期20-23,共4页Machine Building & Automation

摘　　要：飞机复材结构连接的趋势是向着无紧固件方向发展,常采用双搭胶接连接,该连接接头处的胶层剪应力分布是分析双搭胶接连接强度和预测整体复材结构失效的关键问题。建立了基于经典弹性理论的复材双搭胶接结构应力分析理论模型,得到了胶层剪应力分布的解析解,并与根据所测得应变提出的基于经典弹性理论和基于经典层压板理论的应力计算方法得出的胶层剪应力分布结果相比较。结果表明:胶层剪应力分布曲线吻合度较高,峰值相差不超过10.9%。The connection without fasteners is the main trend in the aircraft composite structure connection.Double lap bonding is often used in it.The strength of the double lap bonding and the failure of the whole composite structure mainly depend on the disfribution of the shear stress in the adhesive layer at the joint.In this paper,a theoretical model for stress analysis of the composite double lap bonded structures is established based on classical elastic theory,and the analytical solution of the shear stress distribution of the rubber layer is obtained.The results are compared with ones obtained by classical elastic theory stress calculation method based on measured strain and classical laminate theory stress calculation method.The results show that the shear stress distribution curve of the rubber layer is of high coincidence,and the difference of peak value is not over 10.9%.

关 键 词：复合材料 胶接 双搭接连接 应变测量 应力计算方法 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]