全部 标题 作者
关键词 摘要

OALib Journal期刊
ISSN: 2333-9721
费用:99美元

查看量下载量

相关文章

更多...
航空学报  2014 

旋翼桨涡干扰噪声开环桨距主动控制研究

DOI: 10.7527/S1000-6893.2014.0045, PP. 2901-2909

Keywords: 直升机,旋翼,桨涡干扰,噪声,自由尾迹,主动控制

Full-Text   Cite this paper   Add to My Lib

Abstract:

直升机在斜下降飞行时旋翼产生的桨涡干扰(BVI)噪声十分严重,桨距主动控制是降低旋翼BVI噪声的有效手段之一.为摸索其对旋翼BVI噪声的影响规律并阐释其机理,开展了开环桨距主动控制对旋翼BVI噪声的影响研究.建立能够计入开环桨距主动控制的旋翼自由尾迹模型,并结合翼型气动力模型及基于FW-H(FfowcsWilliams-Hawkings)方程的旋翼载荷噪声计算模型,建立旋翼BVI噪声开环主动控制模型.以40%缩比的4桨叶BO-105直升机模型旋翼为算例,在风洞配平状态下开展开环桨距主动控制对旋翼BVI噪声的影响研究.通过分析算例旋翼在不同相位、幅值的桨距主动控制下的BVI噪声声压级、桨盘气动载荷及桨盘迎角分布,总结出开环桨距主动控制影响旋翼BVI噪声的规律,并初步阐释了其机理适当的桨距主动控制可改善桨盘迎角分布,降低桨涡干扰位置附近的桨叶气动载荷,从而降低BVI噪声.

References

[1]  Shi Y J, Zhao Q J, Xu G H. Numerical calculation and parametric study of aerodynamics of blade-vortex interaction[J]. Acta Aeronautica et Astronautica Sinica, 2010,31(6): 1106-1114. (in Chinese) 史勇杰, 招启军, 徐国华. 旋翼桨-涡干扰气动特性计算及参数影响研究[J]. 航空学报, 2010, 31(6): 1106-1114.
[2]  Shi Y J, Xu G H. Research on the influence of flight parameters on the helicopter rotor BVI noise characteristics[J]. Acta Aeronautica et Astronautica Sinica, 2013,34(11): 2520-2528. (in Chinese) 史勇杰, 徐国华. 飞行参数对旋翼桨-涡干扰噪声特性的影响机理研究[J]. 航空学报, 2013, 34(11): 2520-2528.
[3]  Shi Y J, Fan F, Xu G H, et al. Rotor blade-vortex interaction noise prediction based upon hybrid CDF[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(1): 91-98. (in Chinese) 史勇杰, 樊枫, 徐国华, 等. 基于混合CFD方法的旋翼桨-涡干扰计算[J]. 航空学报, 2011, 32(1): 91-98.
[4]  Bagai A, Leishman J G. Rotor free wake modeling using pseudo implicit technique including comparisons with experimental data[J]. Journal of the AHS, 1995, 40(3): 29-41.
[5]  Wang C, Lu Y. Analysis of aerodynamic characteristics of electrically controlled rotor based on free wake model[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2011, 43(3): 324-329. (in Chinese) 王超, 陆洋. 基于自由尾迹方法的电控旋翼气动特性分析[J]. 南京航空航天大学学报, 2011, 43(3): 324-329.
[6]  Song C Y. Computation of rotational noise and research of blade-vortex interaction noise for rotors based upon wake analysis[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010, 11-73. (in Chinese) 宋辰瑶. 基于尾迹分析的旋翼旋转噪声计算及桨-涡干扰噪声研究[D]. 南京: 南京航空航天大学, 2010, 11-73.
[7]  Yin J P, Hu Z W. Prediction of rotor blade vortex interaction noise form measured unsteady surface pressure of blade[J]. Acta Aeronautica et Astronautica Sinica, 1996, 17(5): 598-600. (in Chinese) 尹坚平, 胡章伟. 用测量的叶片表面非定常压力预估直升机旋翼桨涡干扰(BVI)噪声[J]. 航空学报, 1996, 17(5): 598-600.
[8]  Farassat F. Derivation of formulations 1 and 1A of Farassat, NASA TM-2007-214853[R]. Washington, D. C.: NASA Langley Research Center, 2007.
[9]  Brentner K S, Farassat F. Modeling aerodynamically generated sound of helicopter rotors[J]. Progress in Aerospace Sciences, 2003, 39(2-3): 83-120.
[10]  Kessler C. Active rotor control for helicopters: individual blade control and swashplateless rotor designs[C]//36th European Rotorcraft Forum. Paris France: European Rotorcraft Forum, 2010, 1: 3-22.
[11]  Yu Y H. Rotor blade-vortex interaction noise[J]. Progress in Aerospace Sciences, 2000, 36(2): 97-115.
[12]  Brooks T F. Studies of blade-vortex interaction noise reduction by rotor blade modification[C]//Proceedings of the 1993 National Conference on Noise Control Williamsburg. Williamsburg VA: NASA Langley Research Center, 1993, 12: 57-66.
[13]  Hoad D R. Evaluation of helicopter noise due to blade-vortex interaction for five tip configurations, NASA TP-1608[R]. Washington, D. C.: NASA Langley Research Center, 1979.
[14]  Bebesel M, Ploz G, Schoell E. Aerodynamic and aeroacousticlayout of the ATR (Advanced Technology Rotor)[C]//American Helicopter Society 55th Annual Forum. Montreal: American Helicopter Society, 1999, 1: 119-129.
[15]  Hardin J C, Lamkin S L. Concepts for reduction of blade vortex interaction noise[J]. Aircraft, 1987, 24(5): 120-125.
[16]  Brooks T F, Booth E R, Jolly J R, et al. Reduction of blade-vortex interaction noise through higher harmonic pitch control[J]. Journal of the American Helicopter Society, 1990,35(1): 86-91.
[17]  Splettstoesser W R, Schultz K J, Kube R, et al. A higher harmonic controltest in the DNW to reduce impulsive bvinoise[J]. Journal of the American Helicopter Society, 1994, 39(4): 3-13.
[18]  Yu Y H, Tung C. The hart II test: rotor wakes and aeroacoustics with higher-harmonic pitch control (HHC) inputs[C]//American Helicopter Society 58th Annual Forum. Montreal: American Helicopter Society, 2002: 1-11.

Full-Text

Contact Us

service@oalib.com

QQ:3279437679

WhatsApp +8615387084133