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| Vibration Isolation Design of Engine Installation System Considering the Influence of Wing Flexibility |
| Received:February 07, 2019 Revised:July 25, 2019 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/ issn.1672-9242.2019.07.012 |
| KeyWord:flexible wing vibration isolation vibration decoupling |
| Author | Institution |
| CHEN Chun-lan |
Aviation Science and Technology Key Laboratory of Aircraft Noise and Vibration Engineering, Aircraft Strength Research Institute of China, Xi′an , China |
| CHEN Yong-hui |
Aviation Science and Technology Key Laboratory of Aircraft Noise and Vibration Engineering, Aircraft Strength Research Institute of China, Xi′an , China |
| YAN Qun |
Aviation Science and Technology Key Laboratory of Aircraft Noise and Vibration Engineering, Aircraft Strength Research Institute of China, Xi′an , China |
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| Abstract: |
| Objective To research the design method of vibration isolation system for turboprop engine installation system under the influences of many factors such as vibration isolation efficiency, vibration mode decoupling and wing flexibility. Methods Firstly, the dynamic characteristics of the two-degree-of-freedom system were theoretically derived, and the importance of the wing flexibility in the vibration isolation analysis of the installation system was obtained. Furthermore, the elastic center theory was applied to the design of engine installation system, and the optimal parameters of the main design variables of the two-plane five-point installation system were obtained. To analyze the influence of the flexible wing on the design process, the finite element method and multi-body dynamics method were used to establish a rigid-flexible hybrid calculation model of the installation system for analysis. Results The damping of the wing had a great influence on the resonance response of the high frequency. Good vibration damping effect can be realized when the vertical stiffness ratio was higher than 2. Conclusion The vibration isolation design method of the mounting system considering wing vibration damping effect and vibration mode decoupling could provide scientific basis for the engineering design of aeroengine mounting system. |
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