某型飞机连接件疲劳试验连接螺栓头失效分析  

Failure Analysis for the Bolt Head of Lap Joint Panel of an Outer Wing in the Fatigue Test

作　　者：刘仁宇[1] 何宇廷[1] 崔荣洪[1] 舒文军[1] 

机构地区：[1]空军工程大学工程学院,西安710038

出　　处：《航空精密制造技术》2008年第5期28-31,共4页Aviation Precision Manufacturing Technology

基　　金：国防"十一五"预研基金资助(513270501)

摘　　要：对某型飞机连接件疲劳试验厚板试件进行受载分析并对典型的脱落螺栓头失效件进行了金相分析,通过试验提出提供更大刚度支持,设计了专门复合夹具,解决了失效问题。研究结果为拉剪搭接形式的航空连接结构件的失效预防提供了试验支持,同时对于厚板连接件的疲劳试验方案的改进具有指导意义。Many bolt heads of an airplane lap joint are pulled out in the fatigue test.The bolt head fractography of a representative bolt is observed and analyzed.Results show that the bolt failure is due to fatigue strength reduction,which is caused by the bending stress induced by the thickness effects and the extrusion stress at cross section.The results are very.significant for the thick-lap-joint fatigue test,meanwhile,the test evidence and theory support are provided for airplane single lap joint to prevent from failure.

关 键 词：连接件 螺栓 断口 疲劳断裂 失效分析 

分 类 号：V229[航空宇航科学与技术—飞行器设计]