飞机副翼传动杆断裂分析  

Failure Analysis of Aileron Driving Rod in Aircraft

作　　者：徐志刚[1] 王朝清[1] 傅国如[1] 张斌飞[2] 

机构地区：[1]北京航空工程技术研究中心 [2]中国人民解放军93911部队

出　　处：《失效分析与预防》2011年第1期50-55,共6页Failure Analysis and Prevention

摘　　要：近年来发生3起飞机副翼传动杆断裂/裂纹故障,普查又发现25根传动杆套筒存在裂纹,此故障严重影响飞行安全。对传动杆断口的宏、微观特征进行观察与分析,测量和计算传动杆与机翼结构间隙和传动杆强度,并进行了飞机地面和空中振动强度测量等工作。结果表明:传动杆A的断裂性质为双向弯曲疲劳断裂,其断裂是由于相连的传动杆B受激振动,与传动杆A振动叠加,产生额外弯曲载荷所致。Several fracture or cracking failures have happened to the aileron driving rods in aircraft. In order to find out the cause, macro and micro observations of the fracture surfaces were carried out, the clearance length between the rod and wing structure and the strength of the rod were caculated, and the vibration amplitude of the rod on the ground and in flight was measured. The results show that the fracture mode of driving rod A is twodirection bending fatigue fracture, and the fracture resulted from the extra bending load, which was caused by the coeffect of its own vibration and the vibration of driving rod B.

关 键 词：副翼 传动杆 断裂/裂纹 双向弯曲疲劳 振动 

分 类 号：V227[航空宇航科学与技术—飞行器设计]