直升机旋翼对尾桨非定常气动载荷的影响

doi:10.7527/S1000-6893.2015.0024

Abstract

Abstract:

Helicopter main rotor tip vortex will penetrate into the tip path plane of tail rotor under hover and side-slip conditions, which results in marked variation of tail rotor unsteady aerodynamic loads. In order to more accurately simulate the variation of tail rotor unsteady aerodynamic loads due to main rotor/tail rotor interaction, time-varying item induced by rotor tip vortex is added into pressure term of panel method, which is used to reflect the influence of the velocity impulse and time-varying geometry of rotor tip vortex on unsteady pressure of rotor blades. Meanwhile, viscous effect of vortex particles method is modified through vortex mirror technique to ensure that the rotor vorticity near blades is constant. Thus, the model of unsteady aerodynamic interaction of rotor wake and tail rotor blade is established, and coupled into panel/viscous vortex particle hybrid method to found the analytical method of tail rotor unsteady airloads under main rotor/tail rotor interaction. The unsteady aerodynamic load of AH-1G rotor blade is predicted and compared with the experiment and computational fluid dynamics (CFD) results to validate the effectiveness of the present unsteady aerodynamic interaction model. The influence of main rotor on unsteady aerodynamic loads of tail rotor blade under hover, crosswind, 60° starboard sideslip is analyzed base on NASA ROBIN (Rotor Body Interaction) model. It is shown that the influence of main rotor wake on unsteady aerodynamic loads of tail rotor blade is significant. The average of tail rotor thrust is decreased and the unsteady airload is increased markedly under the main rotor/tail rotor interaction in hover. The "vortex ring" of tail rotor in portside crosswind is weakened by the main rotor/tail rotor interaction, and the tail rotor thrust and unsteady airloads are significantly increased. The damage of tail rotor thrust is the most prominent in 60° starboard sideslip, a phenomenon called "rapid recovery" is observed under low speed sideslip condition, and the amplitude of unsteady airloads of tail rotor is markedly increased due to the main rotor/tail rotor interaction.

Key words: unsteady aerodynamic interaction, aerodynamic loads, viscous vortex particle method, main rotor, tail rotor

CLC Number:

V211.52

TAN Jianfeng. Influence of helicopter rotor on tail rotor unsteady aerodynamic loads[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(10): 3228-3240.

References

[1] Leishman J G. Principles of helicopter aerodynamics[M]. 2nd ed. New York: Cambridge University Press, 2006: 658-682.
[2] Wiesner W, Kohler G. Tail rotor performance in presence of main rotor, ground, and winds[J]. Journal of the American Helicopter Society, 1974, 19(3): 2-9.
[3] Livingston C L, Murphy M R. Flying qualities considerations in the design and development of the HueyCobra[J]. Journal of the American Helicopter Society, 1969, 14(1): 49-66.
[4] Prouty R W, Amer K B. The YAH-64 empennage and tail rotor-a technical history[C]//38th American Helicopter Society Annual Forum. Fairfax VA: AHS, 1982: 247-261.
[5] Ellin A D S. Lynx main rotor/tail rotor interactions: mechanisms and modeling[J]. Journal of Aerospace Engineering, 1994, 208(2): 115-128.
[6] Sheridan P F, Smith R P. Interactional aerodynamics—a new challenge to helicopter technology[J]. Journal of the American Helicopter Society, 1980, 25(1): 3-21.
[7] George A R, Chou S T. A comparative study of tail rotor noise mechanisms[J]. Journal of the American Helicopter Society, 1986, 31(4): 36-42.
[8] Srinivas V, Chopra I, Haas D, et al. Prediction of tail rotor thrust and yaw control effectiveness[J]. Journal of the American Helicopter Society, 1995, 40(4): 34-43.
[9] Cuzieux F, Basset P M, Desopper A. Modeling of loss of tail rotor effectiveness conduction to unanticipated yaw[C]//28^th International Congress of the Aeronautical Sciences(ICAS). Brisbane, Australia: ICAS, 2012: 1-11.
[10] Quackenbush T R, Bliss D B. Prediciton of high-resolution flowfields for rotorcraft aeroacoustics[J]. AIAA Journal, 1991, 29(11): 1778-1786.
[11] Yin J P, Ahmed S R. Aerodynamics and aeroacoustics of helicopter main-rotor/tail-rotor interaction[C]//15^th Aerodynamic Decelerator Systems Technology Conference. Reston: AIAA, 1999: 1-13.
[12] Yin J P, Hu Z W. Numerical simulation on interaction of the free wake of helicopter main and tail rotor[J]. Acta Aerodynamic Sinica, 1998, 16(4): 406-410 (in Chinese). 尹坚平, 胡章伟. 直升机主、尾桨自由尾迹相互干扰的数值模拟[J]. 空气动力学学报, 1998, 16(4): 406-410.
[13] Dietz M, Kneisch T, Roth G. EC145 T2: comprehensive and challenging industrial CFD applications[C]//Proceeding of American Helicopter Society International 68^th Annual Forum. Fairfax VA: AHS, 2012: 1-10.
[14] Lee B S, Choi J H, Kwon O J. Numerical simulation of free-flight rockets air-launched from a helicopter[J]. Journal of Aircraft, 2011, 48(5): 1766-1775.
[15] Wang B, Zhao Q J, Xu G H. Numerical analysis on noise of rotor with unconventional blade tips based on CFD/Kirchhoff method[J]. Chinese Journal of Aeronautics, 2013, 26(3): 572-582.
[16] Zhao M, Cao Y H. Numerical simulation of rotor flow field based on overset grids and several spatial and temporal discretization schemes[J]. Chinese Journal of Aeronautics, 2012, 25(2) : 155-163.
[17] Komerath N M, Smith M J, Tung C. A review of rotor wake physics and modeling[J]. Journal of the American Helicopter Society, 2011, 56(2): 022006-1-21.
[18] Biava M, Khier W, Vigevano L. CFD prediction of airflow past a full helicopter configuration[J]. Aerospace Science and Technology, 2012, 19(1): 3-18.
[19] He C J, Zhao J G. Modeling rotor wake dynamics with viscous vortex particle method[J]. AIAA Journal, 2009, 47(4): 902-915.
[20] Wei P, Shi Y J, Xun G H, et al. Numerical method for simulating rotor flow field based upon viscous vortex model[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(5): 771-780 (in Chinese). 魏鹏, 史勇杰, 徐国华, 等. 基于黏性涡模型的旋翼流场数值方法[J]. 航空学报, 2012, 33(5): 771-780.
[21] Tan J F, Wang H W. Simulating unsteady aerodynamics of helicopter rotor with panel/viscous vortex particle method[J]. Aerospace Science and Technology, 2013, 30(1): 255-268.
[22] Degond P, Gallic S M. The weighted particle method for convection-diffusion equations. part1. the case of an isotropic viscosity[J]. Mathematics of Computation, 1989, 53: 485-507.
[23] Cottet G H, Koumoutsakos P. Vortex methods theory and practice[M]. Cambridge: Cambridge University Press, 2000: 158-172.
[24] Lorber P F, Egolf T A. An unsteady helicopter rotor-fuselage aerodynamic interaction analysis[J]. Journal of the American Helicopter Society, 1990, 35(3): 32-42.
[25] Cross J L, Watts M E. Tip aerodynamics and acoustics test: a report and data survey, NASA-RP-1179[R]. California: NASA, 1988.
[26] Jee W K, Soo H P, Yung H Y. Euler and navier-stokes simulations of helicopter rotor blade in forward flight using an overlapped grid solver[C]//19th AIAA Computational Fluid Dynamics. Reston: AIAA, 2009: 1-12.
[27] Raymond E M, Susan A G. Steady and periodic pressure measurements on a generic helicopter fuselage model in the presence of a rotor, NASA-TM-2000-210286[R]. California: NASA, 2000.
[28] Filippone A, Afgan I. Orthogonal blade-vortex interaction on a helicopter tail rotor[J]. AIAA Journal, 2008, 46(6): 1476-1489.

Influence of helicopter rotor on tail rotor unsteady aerodynamic loads

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 13

Recommended Articles

Metrics

Comments

[1]	WAN Haoyun, HAN Dong, ZHANG Yuhang. Performance improvement of variable speed tail rotors by passively extendable chord [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(2): 224981-224981.
[2]	TAN Jianfeng, WANG Haowen, WU Chao, LIN Changliang. Rotor/Empennage Unsteady Aerodynamic Interaction with Unsteady Panel/Viscous Vortex Particle Hybrid Method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(3): 643-656.
[3]	Hu Changrong. THE OPTIMIZATION OF LOAD EQUATION DURING AIRCRAFT FLIGHT LOAD MEASUREMNT [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 102-105.
[4]	Sun Jianhua;Qu Shihong. ASTUDY ON FLIGHT LOAD ESTIMATION OF AIRCRAFT STRUCTURAL COMPONENTS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 106-108.
[5]	SunJianhua;QuShihong. A STUDY ON A PARAMETRIC IDENTIFICATION METHOD OF FLIGHT LOAD [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 109-112.
[6]	Hu Changrong. THE OPTIMIZATION OF LOAD EQUATION DURING AIRCRAFT FLIGHT LOAD MEASUREMNT [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 1(1): 102-105.
[7]	Sun Jianhua;Qu Shihong. ASTUDY ON FLIGHT LOAD ESTIMATION OF AIRCRAFT STRUCTURAL COMPONENTS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 1(1): 106-108.
[8]	SunJianhua;QuShihong. A STUDY ON A PARAMETRIC IDENTIFICATION METHOD OF FLIGHT LOAD [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 1(1): 109-112.
[9]	Wang Zhongyan. THE INFLUENCE OF AIRPLANE CONTROL SYSTEM PROPERTIES ON THE MANEUVER LOADS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 27-31.
[10]	Deng Lidong;Xu Chunsheng;Dong Xiurong. ANALYTICAL INVESTIGATION OF THE AIRCRAFT FLIGHT LOADS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 32-35.
[11]	Wang Zhongyan. THE INFLUENCE OF AIRPLANE CONTROL SYSTEM PROPERTIES ON THE MANEUVER LOADS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 1(1): 27-31.
[12]	Deng Lidong;Xu Chunsheng;Dong Xiurong. ANALYTICAL INVESTIGATION OF THE AIRCRAFT FLIGHT LOADS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 1(1): 32-35.
[13]	Yan Heng-yuan;Zheng Quan. NUMERICAL CALCULATION FOR SUBSONIC AND SUPERSONIC AERODYNAMIC LOAD AROUND VEHICLE [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1993, 14(6): 294-298.