Design of a Novel Combined Vibration Absorber Based on the Dynamic Vibration Absorption Principle and Its Application in Helicopters

JIN Kunjian; FU Shuo; XIONG Bo; ZHOU Ruchuan; YU Guorui

doi:10.21656/1000-0887.460109

Volume 47 Issue 3

Mar. 2026

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Article Navigation > Applied Mathematics and Mechanics > 2026 > 47(3): 288-300

JIN Kunjian, FU Shuo, XIONG Bo, ZHOU Ruchuan, YU Guorui. Design of a Novel Combined Vibration Absorber Based on the Dynamic Vibration Absorption Principle and Its Application in Helicopters[J]. Applied Mathematics and Mechanics, 2026, 47(3): 288-300. doi: 10.21656/1000-0887.460109

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Design of a Novel Combined Vibration Absorber Based on the Dynamic Vibration Absorption Principle and Its Application in Helicopters

doi: 10.21656/1000-0887.460109

China Helicopter Research and Development Institute, Jingdezhen, Jiangxi 333001, P.R.China

Received Date: 2025-05-30
Rev Recd Date: 2025-07-04
Publish Date: 2026-03-01

Abstract

Abstract

Multi-order vibration loads on helicopter rotor systems are the main source inducing airframe vibrations, and conventional 1-way vibration absorbers are difficult to balance the multi-direction vibration requirements in flapping and lag directions. To reduce the 5/REV flapping loads and 6/REV lead lag loads on helicopter rotor systems at the same time, a combined vibration absorber for helicopter blades was proposed and designed. Firstly, the vibration reduction performance of the combined vibration absorber was verified through the rotation test of the ground test bench. Secondly, a theoretical analysis model for the combined vibration absorber was established. Finally, with the rotor system vibration response as the assessment index, the vibration reduction performance analysis of the combined vibration absorber was carried out. The results show that, when the rotor system is equipped with a combined absorber, the vibration response under the 6/REV lead lag loads can be reduced by 76.1% and that under the 5/REV flapping loads can be reduced by 53% in the condition that the weight increase ratio of the rotor system is only 7.4%, and the comprehensive damping efficiency can reach 63.5%.
- helicopter,
- rotor system,
- vibration load,
- combined vibration absorber,
- vibration reducing performance

(Recommended by LIU Shaobao, M.AMM Editorial Board)

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References(17)

References

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