直升机高频吸振器性能测试试验方法研究

Research on Performance Test Method for Helicopter High Frequency Vibration Absorber

目的研究直升机主减速器撑杆处高频吸振器性能测试试验方法,从而探究吸振器的减振效果。方法首先建立高频吸振器的减振性能评价分析模型;其次利用“小松鼠”主减速器平台搭建试验台架系统,给出针对直升机高频试验的设计要求及思路,阐述试验原理、试验方案及试验内容;最后利用试验台架系统研究拧紧力矩、激励位置、激励方式对试验测试结果的影响。结果吸振器的安装频率受拧紧力矩的影响很小,试验时保持在4~14N·m即可。不同的激励位置对试验结果有很大影响,为了减小直升机主减速器结构间隙对振动传递的影响,激励位置应选择与撑杆直接连接的壳体上。试验时激励方式应选择白噪声激励,可为试验系统输入宽频稳定的能量。结论该高频吸振器性能测试试验方法真实可行,可为直升机主减速器减振设计提供指导。

The work aims to design a method to test the performance of the high frequency vibration absorber at the main reducer bar of the helicopter,so as to explore the damping effect of the absorber.Firstly,the evaluation and analysis model of the damping effect of high frequency vibration absorber was established.Secondly,the"Little Squirrel"main reducer platform was used to build the test bench system,the design requirements and ideas for the high frequency test of helicopter were given,and the test principle,test scheme and test content were expounded.Finally,the effect of tightening torque,excitation position and excitation mode on test results was studied by the test bench system.The installation frequency of the vibration absorber was very little affected by the tightening torque,and it could be kept at 4~14 N·m during the test.Different excitation positions had great effect on the test results.In order to reduce the effect of the structural clearance of the main reducer of helicopter on vibration transmission,the exciting position should be located on the shell directly connected with the bar.The excitation method should be white noise excitation,which could input broad and stable energy for the test system.The performance test method of high frequency vibration absorber proposed in this work is true and feasible,which can provide guidance for the vi-bration reduction design of main reducer of helicopter.