某直升机尾桨桨距操纵轴缺陷容限试验件失效分析  

Failure Analysis of Flaw Tolerance Test for a HelicopterTail Rotor Sliding Collar

作　　者：黄艳松 王豪 李坚 许维森 HUANG Yansong;WANG Hao;LI Jian;XU Weisen(Equipment Department of PLA Navy,Beijing 100070,China;HuNan Power Machinery Research Institute of AECC,Zhuzhou 412000,China)

机构地区：[1]海军装备部,北京100070 [2]中国航发湖南动力机械研究所,湖南株洲412000

出　　处：《直升机技术》2022年第3期43-46,54,共5页Helicopter Technique

摘　　要：某直升机尾桨桨距操纵轴在缺陷容限试验中非应力关键部位出现裂纹。对桨距操纵轴实际受载情况进行了全面分析,采用有限元法计算了失效部位应力。分析结果表明,在该缺陷容限试验条件下,即盐雾腐蚀坑与螺栓拧紧力矩缺失的共同作用下,裂纹的出现是合理的。分析结果可为其它型号进行缺陷容限设计与验证提供参考。A crack occurred in flaw tolerance test for non-stress critical area of a helicopter tail rotor sliding collar.Load of sliding collar was roundly analyzed.Stress in the area where crack was located was calculated by FEA method.Result showed that the failure was reasonable,for the effect of both corrosion pit and loss of tightening torque.The conclusion could provide reference to other flaw tolerance design and substantiation.

关 键 词：桨距操纵轴 缺陷容限 失效分析 

分 类 号：V216.11[航空宇航科学与技术—航空宇航推进理论与工程]