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
1.Hunan Aeroengine Research Institute， Aero Engine Corporation of China， Zhuzhou 412002， China;2.College of Energy and Power， Nanjing University of Aeronautics and Astronautics， Nanjing 210016， China
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 natural 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 natural 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.
邹亚晨,王平,倪徳,单卫东,臧朝平,张根辈.直升机尾传动轴系的非线性刚度参数辨识方法[J].动力学与控制学报,2020,18(6):77~83; Zou Yachen, Wang ping, Ni De, Shan Weidong, Zang Chaoping, Zhang Genbei. A METHOD FOR IDENTIFYING NONLINEAR STIFFNESS OF HELICOPTER TAIL DRIVE SHAFT SYSTEM[J]. Journal of Dynamics and Control,2020,18(6):77-83.复制