一种耳片连接螺栓的疲劳分析方法  

A Fatigue Analysis Method for Bolt Used in Lugs Connection

作　　者：张帅 李宝珠 刘海涛 ZHANG Shuai;LI Bao-zhu;LIU Hai-tao(Engineering Technology Department,AVIC XAC Commercial Aircraft Co.,Ltd.,Xi'an 710089,China)

机构地区：[1]中航西飞民用飞机有限责任公司工程技术中心,西安710089

出　　处：《西安航空学院学报》2021年第3期19-23,35,共6页Journal of Xi’an Aeronautical Institute

摘　　要：航空工业生产实践和试验结果表明,承受拉应力连接螺栓疲劳源的位置易出现在螺纹区和螺栓头圆角区,而承受剪切力的连接螺栓疲劳源的位置可出现在螺栓的光杆区。基于细节疲劳额定值方法对以承受剪切力为主的耳片连接螺栓进行应力分析,提出了一种耳片连接螺栓的疲劳分析方法。分析结果表明,耳片连接螺栓最高应力点位于螺栓光杆区剪切力产生的弯矩最大的截面上。以某型飞机的耳片连接结构进行疲劳试验,试验结果与分析结果相吻合,耳片连接螺栓光杆区在循环载荷下出现明显磨损。此外,通过试验结果拟合可得到连接螺栓的磨损系数,在此基础上可用提出的方法对以承受剪切力为主的螺栓进行疲劳分析。Based on the detailed fatigue rating method,the paper applies a fatigue analysis method to analyze the stress distribution of lug connecting bolts mainly subjected to shear force.The results show that the highest stress point of the lug connecting bolt is located in the section with the largest bending moment generated by the shear force in the bolt rod area.The fatigue test was carried out with the lug connection structure of a certain type of aircraft.The experimental results were consistent with that analyzed.The rod area of the lug connection bolt showed obvious wear under cyclic load.In addition,the wear coefficient of the connecting bolt is obtained by fitting the test results,and the proposed method can be used to analyze the fatigue of the bolt mainly subjected to shear force.

关 键 词：疲劳分析 细节疲劳额定值 连接螺栓 耳片 

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]