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| Research on Performance Test Method for Helicopter High Frequency Vibration Absorber |
| Received:February 26, 2024 Revised:March 26, 2024 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/issn.1672-9242.2024.07.016 |
| KeyWord:helicopter main retarder bar high frequency absorber |
| Author | Institution |
| SUN Weibing |
China Helicopter Research and Development Institute, Jiangxi Jingdezhen , China |
| SU Hongqing |
China Helicopter Research and Development Institute, Jiangxi Jingdezhen , China |
| WANG Fengjiao |
China Helicopter Research and Development Institute, Jiangxi Jingdezhen , China |
| MA Kun |
China Helicopter Research and Development Institute, Jiangxi Jingdezhen , China |
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| Abstract: |
| The work aims to design a method to test the performance of the high frequency vibration absorber at the main reducer bar of the helicopter, so as to explore the damping effect of the absorber. Firstly, the evaluation and analysis model of the damping effect of high frequency vibration absorber was established. Secondly, the "Little Squirrel" main reducer platform was used to build the test bench system, the design requirements and ideas for the high frequency test of helicopter were given, and the test principle, test scheme and test content were expounded. Finally, the effect of tightening torque, excitation position and excitation mode on test results was studied by the test bench system. The installation frequency of the vibration absorber was very little affected by the tightening torque, and it could be kept at 4~14 N.m during the test. Different excitation positions had great effect on the test results. In order to reduce the effect of the structural clearance of the main reducer of helicopter on vibration transmission, the exciting position should be located on the shell directly connected with the bar. The excitation method should be white noise excitation, which could input broad and stable energy for the test system. The performance test method of high frequency vibration absorber proposed in this work is true and feasible, which can provide guidance for the vibration reduction design of main reducer of helicopter. |
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