Design of a Novel Combined Vibration Absorber Based on the Dynamic Vibration Absorption Principle and Its Application in Helicopters
-
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%.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%.
-
Key words:
- helicopter /
- rotor system /
- vibration load /
- combined vibration absorber /
- vibration reducing performance
edited-byedited-by1) (我刊编委刘少宝推荐) -
图 1 直升机旋翼吸振简化系统
Figure 1. The simplified system of helicopter rotor vibration absorption
图 2 组合吸振器整体结构组成
Figure 2. The overall structure composition of the combined vibration absorber
图 3 挥舞方向吸振器结构组成
Figure 3. The structural composition of the flapping directional vibration absorber
图 4 摆振方向吸振器结构组成
Figure 4. The structural composition of the lag directional vibration absorber
图 10 组合吸振器减振分析流程
Figure 10. The vibration reduction analysis flowchart of the combined absorber
图 11 组合吸振器减振性能仿真分析对比
Figure 11. Comparison of vibration reduction performances of the combined vibration absorber
图 12 组合吸振器减振性能仿真分析与实测对比
Figure 12. Comparison of vibration reduction performances of the combined vibration absorber between simulation and experiment
表 1 组合吸振器结构参数
Table 1. Structural parameters of combined vibration absorber
type parameter design value flapping directional vibration absorber vibration absorption capacity /N 1 000 work angle /(°) ≤15 effective working weight /kg 2 vibration absorber weight/kg 5.4 installation position on the blade /mm 1 105 equivalent pendulum length /mm 28 lag directional vibration absorber vibration absorption capacity /N 1 000 work angle /(°) ≤15 effective working weight /kg 3 vibration absorber weight/kg 6.5 installation position on the blade /mm 1 105 aperture diameter /mm 52 pin diameter /mm 20 equivalent pendulum length /mm 32 
下载: 导出CSV
表 2 组合吸振器主要零部件材料参数
Table 2. Main component material parameters of the combined vibration absorber
serial number name material elastic modulus/GPa Poisson’s ratio density/(kg/m3) 1 rocker 30CrMnSiA 195 0.3 7 750 2 rotation shaft 35Cr2Ni4MoA 195 0.24 7 850 3 bolt standard parts 205 0.3 7 750 4 pendulum ball Gb-4 305 0.3 17 400 5 housing 7050 71.7 0.33 2 740 6 support arm 7050 71.7 0.33 2 740 7 lag body 30CrMnSiA 196 0.3 7 750
下载: 导出CSV
表 3 组合吸振器减振效果试验
Table 3. Vibration reduction effect test of combined absorber
state Z-direction vibration (flapping direction 5th order) X-direction vibration (lag direction 6th order) no combination vibration absorber installed /g 0.9 0.71 a combined vibration absorber installed/g 0.38 0.17 vibration reduction performance /% 57.7 76.1
下载: 导出CSV
表 4 组合吸振器减振性能仿真分析
Table 4. Simulation analysis of vibration reduction performance of the combined absorber
state acceleration at installation position 1/2 peak to peak value no flapping vibration absorber installed /g 0.9 a flapping vibration absorber installed /g 0.545 vibration reduction performance /% 39.5 no lag vibration absorber installed /g 0.7 a lag vibration absorber installed /g 0.222 vibration reduction performance /% 68.3
下载: 导出CSV
表 5 不同有效摆长的减振性能对比
Table 5. Comparison of vibration reduction performances with different equivalent pendulum lengths
l/mm 24 26 28 30 basic response /g 0.9 a vibration absorber installed /g 0.646 0.596 0.545 0.594 vibration reduction effect /% 28.2 33.8 39.5 34
下载: 导出CSV
-
[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. doi: 10.4050/JAHS.20.9 [5] PAUL W F. Development and evaluation of the main rotor bifilar absorber[C]//Proceedings of the American Helicopter Society 25 th 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. -
计量
- 文章访问数: 71
- HTML全文浏览量: 18
- PDF下载量: 10
- 被引次数: 0
渝公网安备50010802005915号