基于动力吸振原理的新型组合吸振器设计及直升机应用

金坤健; 符烁; 熊波; 周如传; 喻国瑞

doi:10.21656/1000-0887.460109

基于动力吸振原理的新型组合吸振器设计及直升机应用

doi: 10.21656/1000-0887.460109

中国直升机设计研究所，江西景德镇 333001

详细信息

作者简介:
金坤健（1973—），男，研究员（E-mail: jinkj@avic.com）;喻国瑞（1989—），男，高级工程师(通信作者. E-mail: yugr@avic.com).

通讯作者:
喻国瑞（1989—），男，高级工程师(通信作者. E-mail: yugr@avic.com).

中图分类号: O328
计量
- 文章访问数: 19
- HTML全文浏览量: 5
- PDF下载量: 4
- 被引次数: 0
出版历程
- 收稿日期: 2025-05-30
- 修回日期: 2025-07-04
- 网络出版日期: 2026-04-01
- 刊出日期: 2026-03-01

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

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

摘要

摘要: 直升机旋翼系统的多阶振动载荷是引发机体振动的主要根源.传统单向吸振器难以兼顾挥舞与摆振方向的多向减振需求，为了同时减小直升机旋翼系统的5阶挥舞载荷和6阶摆振载荷，达到降低全机垂向和面内振动水平的目的，提出并设计了一种直升机桨叶组合吸振器.本文首先通过地面台架的旋转结构设计，开展了组合吸振器减振性能试验；其次建立了组合吸振器的理论分析模型；最后以旋翼系统振动响应为考核指标，开展组合吸振器减振性能分析.研究结果表明：旋翼系统加装组合吸振器后，在旋翼系统仅增重7.4%的条件下，旋翼6阶摆振方向振动响应可以降低76.1%，旋翼5阶挥舞方向振动响应可以降低53%，综合减振效率可达63.5%.
- 直升机 /
- 旋翼系统 /
- 振动载荷 /
- 组合吸振器 /
- 减振性能
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

HTML全文

参考文献(17)

［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.

施引文献

资源附件(0)

访问统计

计量

文章访问数: 19
HTML全文浏览量: 5
PDF下载量: 4
被引次数: 0

姓名
邮箱
手机号码
标题
留言内容
验证码

留言板

基于动力吸振原理的新型组合吸振器设计及直升机应用

doi: 10.21656/1000-0887.460109

作者简介:
金坤健（1973—），男，研究员（E-mail: jinkj@avic.com）;喻国瑞（1989—），男，高级工程师(通信作者. E-mail: yugr@avic.com).

通讯作者:
喻国瑞（1989—），男，高级工程师(通信作者. E-mail: yugr@avic.com).

计量

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

计量

目录

留言板

基于动力吸振原理的新型组合吸振器设计及直升机应用

doi: 10.21656/1000-0887.460109

作者简介: 金坤健（1973—），男，研究员（E-mail: jinkj@avic.com）;喻国瑞（1989—），男，高级工程师(通信作者. E-mail: yugr@avic.com).

通讯作者: 喻国瑞（1989—），男，高级工程师(通信作者. E-mail: yugr@avic.com).

计量

出版历程

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

计量

出版历程

目录

作者简介:
金坤健（1973—），男，研究员（E-mail: jinkj@avic.com）;喻国瑞（1989—），男，高级工程师(通信作者. E-mail: yugr@avic.com).

通讯作者:
喻国瑞（1989—），男，高级工程师(通信作者. E-mail: yugr@avic.com).