直升机尾传动轴系的非线性刚度参数辨识方法  

A METHOD FOR IDENTIFYING NONLINEAR STIFFNESS OF HELICOPTER TAIL DRIVE SHAFT SYSTEM

作　　者：邹亚晨 王平 倪徳 单卫东 臧朝平[2] 张根辈[2] Zou Yachen;Wang ping;Ni De;Shan Weidong;Zang Chaoping;Zhang Genbei(Hunan Aeroengine Research Institute,Aero Engine Corporation of China,Zhuzhou 412002,China;College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国航发湖南动力机械研究所,株洲412002 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《动力学与控制学报》2020年第6期77-83,共7页Journal of Dynamics and Control

摘　　要：提出了基于测试数据来识别尾传动轴系非线性刚度参数的方法.首先,对尾传动轴系进行低幅值激励下的模态测试,并建立尾传动轴系的简化模型,与试验结果对比验证模型的准确性.然后,对尾传动轴系开展不同激励水平下的步进正弦扫频测试,基于测试频响函数得到固有频率随位移幅值的变化关系.对建立的尾传动轴系简化模型进行有限元迭代计算,可以识别出固有频率随等效刚度的变化关系.最终建立起尾传动轴系等效刚度与位移幅值的关系,识别出尾传动轴系的非线性刚度参数.A parameter identification method based on test data was proposed to evaluate the nonlinear stiffness of a tail drive shaft system.Firstly,modal testing on the tail drive shaft system under low-amplitude excitation was carried out,and a simplified dynamic model of the tail drive shaft system was established,which was verified by testing results.Then,the stepping sine sweep testing under different excitation levels was conducted,and the relationship between nat⁃ural frequency and displacement amplitude was obtained based on the measured frequency response function.Moreover,the finite element iterative calculation of the simplified model was carried out to achieve the relationship between the nat⁃ural frequency and the equivalent stiffness of the tail drive shaft system.Finally,the relationship between the equivalent stiffness and the displacement amplitude was established,and the nonlinear stiffness of the tail drive shaft system was identified.

关 键 词：直升机尾传动轴系 频响函数 模态测试 非线性刚度 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]