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

Turn off MathJax

Article Contents

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

Citation:

PDF( 3230 KB)

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

Available Online: 2026-04-01

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

FullText(HTML)

References(17)

References

［1］张呈林, 张晓谷, 郭士龙. 直升机部件设计[M]. 北京: 航空专业教材编审组, 1986.（ZHANG Chenglin, ZHANG Xiaogu, GUO Shilong.Design of Helicopter Components[M]. Beijing: Editorial and Review Team for Aviation Professional Textbooks,1986.(in Chinese)）

［2］孙之钊. 直升机强度[M]. 南京: 南京航空航天大学, 1995.(SUN Zhizhao.Helicopter Strength[M]. Nanjing: Nanjing University of Aeronautics and Astronautics, 1995.(in Chinese))

［3］张晓谷. 直升机动力学设计[M]. 北京: 航空工业出版社, 1995.（ZHANG Xiaogu.Helicopter Dynamics Design[M]. Beijing: Aviation Industry Press, 1995. (in Chinese)）

［4］AMER K B，NEFF J R. Verticalplane pendulum absorbers[J].Journal of the American Helicopter Society, 1975, 20(3): 917.

［5］PAUL W F. Development and evaluation of the main rotor bifilar absorber\[C\]//Proceedings of the American Helicopter Society 25th Annual Forum, 1969: 364372.

［6］JOHNSON W.Rotorcraft Aeromechanics[M]. 2nd ed. United Kingdom. Cambridge University Press, 2022.

［7］唐梓杰. 共轴刚性旋翼桨毂双线摆动力吸振研究[D]. 南京: 南京航空航天大学, 2022.(TANG Zijie. Research on vibration reduction of coaxial rigid rotor hub by bifilar pendulum dynamic absorber[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2022. (in Chinese))

［8］熊波, 陈卫星, 刘光, 等. 桨毂双线摆式动力吸振器减振性能探究试验[J]. 科技与创新, 2022(5): 4345.(XIONG Bo, CHEN Weixing, LIU Guang, et al. Experimental study on vibration reduction performance of dualpendulum dynamic vibration absorber rotor hub[J].Science and Technology & Innovation, 2022(5): 4345. (in Chinese))

［9］袁曦. 桨毂双线摆吸振器试验台及其动力控制系统设计[D]. 南京: 南京航空航天大学, 2021.(YUAN Xi. Design of bifilar pendulum absorber test bench and it’s power control system[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2021. (in Chinese))

［10］戴露豪. 双线摆吸振器试验装置设计与验证[D]. 南京: 南京航空航天大学, 2019.(DAI Luhao. Design and verification of experimental device for bifilar pendulum absorber[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in Chinese))

［11］符烁, 方科, 喻国瑞, 等. 直升机桨叶挥舞单摆吸振器吸振性能研究[J]. 直升机技术, 2024(2): 2630.(FU Shuo, FANG Ke, YU Guorui, et al. The study on vibration reducing performance of helicopter blade flapwise pendulum absorbers[J].Helicopter Technique, 2024(2): 2630. (in Chinese))

［12］王正峰, 黄国科. 直升机旋翼桨根单摆吸振器载荷计算方法[J]. 直升机技术, 2021(2): 2932.(WANG Zhengfeng, HUANG Guoke. Loads prediction of helicopter rotor blade absorber[J].Helicopter Technique, 2021(2): 2932. (in Chinese))

［13］陈浩, 马小艳, 王之瑞. 动力吸振器在直升机减振上的应用及效果验证[J]. 直升机技术, 2024(2): 14.(CHEN Hao, MA Xiaoyan, WANG Zhirui. Application and effect verification of dynamic vibration absorber in helicopter vibration reduction[J].Helicopter Technique, 2024(2): 14. (in Chinese))

［14］鲍泽源, 丁晓红, 李海东, 等. 粉末颗粒阻尼器阻尼性能的影响因素分析[J]. 机械设计与研究, 2024, 40(6): 110115.(BAO Zeyuan, DING Xiaohong, LI Haidong, et al. Influence factors of damping performance in particle dampers[J].Machine Design & Research, 2024, 40(6): 110115. (in Chinese))

［15］胡龙轩. 颗粒阻尼动力吸振器减振性能的实验研究[D]. 南昌: 南昌航空大学, 2022.(HU Longxuan. Experimental research on vibration reduction performance of particle damping dynamic vibration absorber[D]. Nanchang: Nanchang Hangkong University, 2022. (in Chinese))

［16］魏武雷, 韩东. 嵌入式挥舞吸振器对旋翼桨叶挥舞载荷的抑制研究[J]. 南京航空航天大学学报, 2017, 49(2): 225230.(WEI Wulei, HAN Dong. Flapwise load reduction of rotor blades by embedded flapwise absorbers[J].Journal of Nanjing University of Aeronautics & Astronautics, 2017, 49(2): 225230. (in Chinese))

［17］JOHNS O D.Analytical Mechanics for Relativity and Quantum Mechanics[M]. Oxford: Oxford University Press, 2005.

Relative Articles

Supplements(0)

Cited By

Proportional views