|
| Vibration Response Prediction Based on Helicopter Coupling Analysis |
| Received:June 30, 2020 Revised:July 08, 2020 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/issn.1672-9242.2020.09.002 |
| KeyWord:helicopter dynamics coupling model vibration response |
| Author | Institution |
| FENG Zhi-zhuang |
Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen , China |
| DAI Zhi-xiong |
Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen , China |
| LIU Chen |
Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen , China |
|
| Hits: |
| Download times: |
| Abstract: |
| The paper aims to predict the vibration response of helicopter. The moderate deflection beam theory was adopted to establish the finite element model of rotor blade. The quasi-steady aerodynamic model and Pitt dynamic inflow theory were used to simulate the aerodynamic force on the rotor wing. Combining the rotor structure and aerodynamic model, the dynamic analysis model of rotor wing was formed, and the correctness of the model was verified by the rotor wing dynamic tests. The helicopter fuselage dynamic model was established based on Patran. According to the results of rotor wing dynamic analysis, the model information of the fuselage was screened and extracted. Coupled rotor dynamics and fuselage dynamics formed the coupling dynamic analysis model of helicopter, which was resolved by time finite element method. The model is used to predict the vibration response of helicopter fuselage and to compare with experimental results. The results show that the vibration response calculated by this method is the same as the test. |
| Close |
|
|
|