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Research on the Effect of Open-loop Active Blade-pitch Control on Rotor BVI Noise Alleviation
Received date: 2013-12-09
Revised date: 2014-04-08
Online published: 2014-05-01
Supported by
National Natural Science Foundation of China (51375229); Youth Science Innovation Foundation of Nanjing University of Aeronautics and Astronautics(NS2013002)
Blade-vortex interaction (BVI) noise is one of the most annoying and intrusive kinds of noise and becomes dominant during skew descent flight, and open-loop active blade pitch control is one of the effective means to reduce BVI noise. A research on the effect of open-loop active blade pitch control on rotor BVI noise alleviation is carried out to find out the influencing rules and to make clear the mechanism of it. The rotor free wake model which could consider the impact of open-loop active blade pitch control is built first, and then open-loop active blade-pitch control on rotor BVI noise alleviation model is established with the rotor aerodynamic model and the rotor loading noise model based on the FW-H (Ffowcs Williams-Hawkings) equation. The research is carried out to investigate the effect of open-loop active blade pitch control on BVI noise level based on a 40-percent geometrically scaled BO-105 helicopter model rotor under wind trim conditions. By analyzing variations of BVI sound pressure level and the distribution of angle of attack on rotor disk when experiencing phase sweep and amplitude sweep control, the influencing rules of active blade pitch control on BVI noise level are summarized, and the mechanism of BVI noise reducing through active blade pitch control is found out: appropriate active blade pitch control could improve the distribution of angle of attack on rotor disc, and then decrease aerodynamic loads where BVI happens, causing the alleviation of BVI noise finally.
Key words： helicopter; rotor; blade-vortex interaction; noise; free wake; active control
FENG Jianbo , LU Yang , XU Jinfa , WANG Chao . Research on the Effect of Open-loop Active Blade-pitch Control on Rotor BVI Noise Alleviation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014 , 35(11) : 2901 -2909 . DOI: 10.7527/S1000-6893.2014.0045
[1] 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.
[2] Yu Y H. Rotor blade-vortex interaction noise[J]. Progress in Aerospace Sciences, 2000, 36(2): 97-115.
[3] 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.
[4] 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.
[5] 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.
[6] Hardin J C, Lamkin S L. Concepts for reduction of blade vortex interaction noise[J]. Aircraft, 1987, 24(5): 120-125.
[7] 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.
[8] 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.
[9] 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.
[10] 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.
[11] 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.
[12] 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.
[13] 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.
[14] 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.
[15] 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.
[16] 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.
[17] Farassat F. Derivation of formulations 1 and 1A of Farassat, NASA TM-2007-214853[R]. Washington, D. C.: NASA Langley Research Center, 2007.
[18] Brentner K S, Farassat F. Modeling aerodynamically generated sound of helicopter rotors[J]. Progress in Aerospace Sciences, 2003, 39(2-3): 83-120.
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