摘要
舰载直升机易受外部机动载荷波动的影响导致水平传动轴和尾斜轴相连接的轴角发生偏差,引起尾传动系统振动超标,严重时会造成尾传动轴断裂甚至坠机等灾难性事故。论文首先推导含轴角参数的尾传动系统振动方程,得到了轴角偏差与啮合刚度的关系,探究了偏差值与尾斜轴振动幅值的内在关联,以某型直升机尾斜传动系统为研究对象,建立尾传动系统动力学模型,揭示了轴角参数对尾斜轴振动特性的影响规律:不同设计角度的尾传动系统在轴角发生偏差时振动响应趋势基本一致,尾斜轴振动幅值会随设计角度的增加而增加;轴角在0°~2°范围内发生偏差时,尾斜轴的振动幅值会呈现先增加后减小的趋势,偏差在1.5°左右时尾斜轴振幅达到最大值。当轴角偏差相同时,尾斜轴上中间减速器处的振动幅值为尾减速器处的3.6倍。研究结果可为直升机尾传动系统动力学设计与振动故障分析提供参考。
The susceptibility of shipborne helicopter to external maneuvering load fluctuation leads to deviation of shaft angle connecting horizontal drive shaft and oblique tail shaft,which leads to excessive vibration of tail drive system,and even catastrophic accidents such as fracture of tail drive shaft in serious cases.This paper first deduces the vibration equation of the tail drive system containing shaft angle parameter,gets the relationship between shaft angle deviation and meshing stiffness,and explores the internal connection between the deviation and tail inclined shaft vibration amplitude.Taking one type of helicopter tail slanting transmission system as the research object,this paper sets up the tail drive system dynamics model and reveals the law of tail shaft angle parameters influence on inclined shaft vibration characteristics:The vibration response trend of tail-drive systems with different design angles is basically the same when the shaft angle deviation occurs,and the vibration amplitude of tail-inclined shaft increases with the increase of design angle.When the shaft angle deviation occurs in the range of 0-2 degrees,the vibration amplitude of the tail-inclined axis increases first and then decreases.When the deviation is about 1.5 degrees,the amplitude of the tail-inclined axis reaches the maximum.When the shaft angle deviation is the same,the vibration amplitude at the middle reducer on the aft oblique shaft is 3.6 times that at the aft reducer.The research results can provide reference for dynamic design and vibration fault analysis of helicopter tail transmission system.
作者
周治港
宾光富
李超
李坚
ZHOU Zhigang;BIN Guangfu;LI Chao;LI Jian(School of Mechanical and Electrical Engineering,Hunan University of Science and Technology,411201 Xiangtan,China;AECC Hunan Power Machinery Research Institute,412002 Zhuzhou,China)
出处
《应用力学学报》
CAS
CSCD
北大核心
2023年第4期901-908,共8页
Chinese Journal of Applied Mechanics
基金
国家自然科学基金资助项目(No.52175091)
湖南省科技创新领军人才资助项目(No.2020RC4039)。
关键词
轴角偏差
啮合刚度
设计角度
尾斜轴
振动响应
舰载直升机
shaft angle deviation
meshing stiffness
design angle
end of inclined shaft
vibration response
shipborne helicopter
