某型飞机外翼下壁板连接件疲劳试验失效分析  

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

作　　者：刘仁宇[1] 何宇廷[1] 舒文军[1] 崔荣红 

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6期42-44,50,共4页Aviation Precision Manufacturing Technology

基　　金：国防"十一五"预研基金资助(513270501)

摘　　要：通过对某型飞机外翼下壁板与肋典型连接厚件疲劳试验的破坏件进行断口金相分析和试验特征分析发现,在多种应力综合作用下,处于三向应力状态下的螺栓孔内壁形成疲劳源,最终发生疲劳断裂,且在出现裂纹之后,裂纹扩展寿命很短。Fractography was observed and test characters were analyzed by test of lap joint panel of an outer wing. It is confirmed that bolt holes generate fatigue regions caused by kinds of tension forces, and accordingly specimens have fatigue failure. It is founded that the crack extension life is very short.

关 键 词：连接件 螺栓 断口 疲劳断裂 金相分析 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]