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

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

Clc Number:

Fund Project:

  • Article
  • |
  • Figures
  • |
  • Metrics
  • |
  • Reference
  • |
  • Related
  • |
  • Cited by
  • |
  • Materials
  • |
  • Comments
    Abstract:

    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.

    Reference
    Related
    Cited by
Get Citation
Share
Article Metrics
  • Abstract:
  • PDF:
  • HTML:
  • Cited by:
History
  • Received:June 19,2019
  • Revised:August 22,2019
  • Adopted:
  • Online: January 05,2021
  • Published:

WeChat

Mobile website