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Influence of higher harmonic control on airload and acoustics of rotor blade-vortex interaction
Received date: 2016-10-13
Revised date: 2017-02-19
Online published: 2017-03-20
Supported by
Funding of Jiangsu Innovation Program for Graduate Education (KYLX16_0389);Priority Academic Program Development of Jiangsu Higher Education Institutions*Corresponding author.E-mail:ghxu@nuaa.edu.cn
Harsh blade-vortex interaction (BVI) noise will be generated when a helicopter is flying at a moderate speed level flight or descending. Based on the modified Beddoes wake/blade structural dynamics coupling model and Farassat 1A formula, a rotor BVI airload and acoustics prediction method is proposed, in which the influence of higher harmonic control (HHC) can be included. The additional tip vortex vertical displacement caused by HHC is derived from time integration of higher harmonic inflow, and a transfer function that relates single HHC input to resulting response at the same and neighboring frequencies is identified by blade dynamic characteristics. The rotor airload of the baseline case in higher harmonic control aeroacoustics rotor Test Ⅱ (HART Ⅱ) is investigated and compared with experimental data firstly. The influencing mechanism and varying pattern of the rotor acoustic property at different 3/Rev control phases is then assessed. The results show that blade dynamic characteristics, especially torsional behaviors, are important for effectiveness of higher harmonic control. Selection of HHC phase input is significant to BVI noise control, and irrational HHC phase input will worsen noise radiation.
WANG Liangquan , XU Guohua , SHI Yongjie , XIA Runze . Influence of higher harmonic control on airload and acoustics of rotor blade-vortex interaction[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(7) : 520847 -520847 . DOI: 10.7527/S1000-6893.2017.520847
[1] HUBBARD H H. Aeroacoustics of flight vehicles: Theory and practice[M]. Melville, NY: American Institute of Physics, 1995.
[2] HARDIN J C, LAMKIN S L. Concepts for reduction of blade-vortex interaction noise[J]. Journal of Aircraft, 1986, 24(2): 120-125.
[3] YU Y H, GMELIN B, SPLETTSTOESSER W, et al. Reduction of helicopter blade-vortex interaction noise by active rotor control technology[J]. Progress in Aerospace Sciences, 1997, 33(9): 647-687.
[4] WOOD E R, POWERS R W, CLINE J H, et al. On developing and flight testing a higher Harmonic control system[J]. Journal of the American Helicopter Society, 1985, 30(1): 3-20.
[5] POLYCHRONIADIS M, ACHACHE M. Higher harmonic control: Flight tests of an experimental system on SA 349 research gazelle[C]//American Helicopter Society Annual Forum, 1986.
[6] WALSH D M. Flight tests of an open loop higher harmonic control system on an S-76A helicopter[D]. BocaRaton: Florida Florida Atlantic University, 1986.
[7] GIOVANETTI E B, HALL K C. Optimum design of compound helicopters that use higher harmonic control[J]. Journal of Aircraft, 2015, 52(5): 1-10.
[8] SPLETTSTOESSER W R, SCHULTZ K J, KUBE R, et al. A higher harmonic control test in the DNW to reduce impulsive BVI noise[J]. Journal of the American Helicopter Society, 1994, 39(4): 3-13.
[9] BOYD D D. HART-Ⅱ acoustic predictions using a coupled CFD/CSD method[C]//American Helicopter Society Annual Forum, 2009.
[10] 杨一栋, 袁卫东. 直升机随机自适应高阶谐波控制抑振研究[J]. 振动工程学报, 1996(2): 177-181. YANG Y D, YUAN W D. Study of helicopter vibration reduction technique with stochastic adaptive HHC[J]. Journal of Vibration Engineering, 1996(2): 177-181 (in Chinese).
[11] 冯剑波, 陆洋, 徐锦法, 等. 旋翼桨-涡干扰噪声开环桨距主动控制研究[J]. 航空学报, 2014, 35(11): 2901-2909. FENG J B, LU Y, XU J F, et al. Research on the effect of open-loop active blade pitch control on rotor BVI noise alleviation[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(11): 2901-2909 (in Chinese).
[12] WALL B G, LIM J W, SMITH M J. An assessment of comprehensive code prediction state-of-the-art using the HART Ⅱ international workshop data[C]//American Helicopter Society Annual Forum, 2012.
[13] WALL B G. Prescribed wake modifications to account for harmonic rotor loading and validation with HART data[C]//American Helicopter Society Annual Forum, 2011.
[14] WALL B G. Helicopter rotor BVI airloads computation using advanced prescribed wake modeling[C]//29th AIAA Applied Aerodynamics Conference, 2011.
[15] BEDDOES T S. A wake model for high resolution airloads[C]//International Conference on Rotorcraft Basic Research, 1985.
[16] LEISHMAN J G. Principles of helicopter aerodynamics[M]. Cambridge: Cambridge University Press, 2006.
[17] BHAGWAT M J, LEISHMAN J G. Generalized viscous vortex model for application to free-vortex wake and aeroacoustic calculations[C]//American Helicopter Society Annual Forum, 2002.
[18] WALL B G. The effect of HHC on the vortex convection in the wake of a helicopter rotor[J]. Aerospace Science & Technology, 2000, 4(5): 321-336.
[19] YUAN K A, FRIEDMANN P P. Aeroelasticity and structural optimization of composite helicopter rotor blades with swept tips: NASA Report 4665[R]. Washington, D.C.: NASA, 1995.
[20] WALL B G. 2nd HHC Aeroacoustic rotor test (HART-Ⅱ)-Part 1: Test documentation: Report IB 111-2003/31[R]. Cologne: German Aerospace Center Institute, 2003.
[21] WILLIAMS J E F, HAWKINGS D L. Sound generation by turbulence and surfaces in arbitrary motion[J]. Philosophical Transactions of the Royal Society of London A: Mathematical, Physical and Engineering Sciences, 1969, 264(1151): 321-342.
[22] FARASSAT F. Derivation of formulations 1 and 1A of Farassat: NASA TM-2007-214853[R]. Washington, D.C.: NASA, 2007.
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