摘要
采用正弦激励对某直升机全尺寸的尾传动轴系进行振动试验,研究了其等效固有频率和阻尼比随激励水平的变化规律;通过不同激励水平正弦扫频试验,获取尾传动轴系的频响函数;基于频响函数辨识等效固有频率和阻尼比随激励水平的变化关系。试验表明:随着激励水平的增大,尾传动轴系的等效固有频率随着位移水平逐渐增大,呈现刚度渐硬的非线性刚度特征;而等效阻尼比则随着速度水平逐渐减小,呈现阻尼非线性特征。该试验方法对于直升机尾传动轴系的动力学设计优化具有重要意义。
The vibration test of a full-scale helicopter tail drive shafting is carried out under sinusoidal excitations,and the variation relationship of its equivalent natural frequency and damping ratio with the excitation level is studied.Through the swept sine tests under different excitation levels,the frequency response functions of the tail drive shafting are abtained,based on which,the variation relationship of the equivalent natural frequency and damping ratio with the excitation level is identified.The experimental results indicate that the equivalent natural frequency of the tail drive shafting increases with the displacement level,which shows the stiffness is hardening nonlinearity.But the equivalent damping ratio decreases with the velocity level,which shows the damping is nonlinear.This experimental method is of great significance for the dynamic design optimization of the helicopter tail drive shafting.
作者
倪德
邹亚晨
王平
周煌亮
张根辈
臧朝平
NI De;ZOU Yachen;WANG Ping;ZHOU Huangliang;ZHANG Genbei;ZANG Chaoping(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;National Key Laboratory of Science and Technology on Helicopter Transmission,Zhuzhou 412002,China;College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《机械制造与自动化》
2021年第4期56-59,85,共5页
Machine Building & Automation
关键词
直升机
尾传动轴系
非线性
刚度
阻尼
helicopter
tail drive shafting
nonlinear
stiffness
damping
