摘要
为了确定某型直升机高频异常振动、尾桨操纵失效故障原因,开展了故障定位和分析工作。通过飞参和振动数据分析,故障定位为传动系统尾传动轴组件水平短轴断裂。以尾水平短轴断裂为顶事件构建故障树,开展故障树分析和底事件验证,确定故障原因为尾水平短轴自激振动发散。开展了尾水平短轴自激振动机理分析,构建了内、外花键齿对接触模型、轴系-花键集总参数模型,进行了尾水平短轴在花键径向摩擦力作用下的稳定性分析,明确了系统失稳条件以及避免系统失稳的措施。开展了尾水平短轴运转动态特性试验,证实了花键副位置润滑不良、法兰盘花键齿面和定位段磨损等条件下会引起自激振动现象。故障机理分析与试验结果表明:花键定位段摩擦是尾水平短轴产生自激振动的基本原因,尾水平短轴自激振动发散,最终导致断裂。该结论可为传动轴设计、维护及故障预防提供参考。
To identify the cause of the high-frequency abnormal vibrations and tail rotor control failure in a certain type of helicopter,fault localization and analysis were conducted.Through analysis of the flight parameters and vibration data,the fault was located as the fracture of the horizontal short shaft in the tail drive shaft assembly of the transmission system.A fault tree was constructed with the fracture of the horizontal short shaft of the tail drive as the top event,and fault tree analysis and bottom event verification were carried out to determine that the fault attributed to the divergence of self-excited vibration in the horizontal short shaft of the tail drive.An analysis of the self-excited vibration mechanism of the tail horizontal short shaft was performed.Contact models for mating internal and external spline teeth pairs,as well as a lumped parameter model for the shafting-spline system,were established.A stability analysis of the horizontal short shaft of the tail drive under the radial friction force of the spline was conducted,clarifying the conditions for system instability and the measures against instability.The dynamic characteristics test of the tail horizontal short shaft was carried out,confirming that self-excited vibration occurred under conditions of inadequate lubrication at the spline pair position,wear on the spline tooth surfaces and locating section of the flange,etc.Analysis of the failure mechanism and test results indicated that the friction in the spline locating section was the fundamental cause of the self-excited oscillation in the horizontal short shaft of the tail drive.The divergence of this self-excited vibration ultimately led to the fracture of the shaft.This finding could provide theoretical guidance for optimizing drive shaft design,maintenance,and failure prevention.
作者
侯波
徐冠峰
袁亮亮
楚晓阳
闫慧娟
HOU Bo;XU Guanfeng;YUAN Liangliang;CHU Xiaoyang;YAN Huijuan(Unit 66037 of the Chinese People’s Liberation Army,Beijing 101121,China;Army Aviation Military Representative Office Stationed in Jingdezhen,Jingdezhen Jiangxi 333001,China)
出处
《航空动力学报》
北大核心
2025年第7期37-44,共8页
Journal of Aerospace Power
关键词
直升机
断裂
尾传动轴
故障分析
自激振动
helicopter
fracture
tail rotor drive shaft
fault analysis
self-excited vibration
