[1]FARASSAT F.Derivation of formulations 1 and 1A of Farassat: NASA TM-2007-214853[R], Hampton, Virginia: Langley Research Center, 2007.
[2]韩忠华, 宋文萍, 乔志德, 等.应用于跨声速旋翼气动声学计算的两种时域方法的比较[J].航空学报, 2006, 27(5):756-62
[3]HAN Z H, SONG W P, QIAO Z D, et al.Comparison of time-domain prediction methods for transonic aeroacoustic noise generated by helicopter rotors[J].Chinese Journal of Aeronautics, 2006, 27(5):756-62
[4]BERNARDINI G, SERAFINI J, GENNARETTI M, et al.Aeroelastic modeling effect in rotor BVI noise prediction[C]//12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference). American Institute of Aeronautics and Astronautics, 2006: 2606.
[5]ZHONG S, ZHOU P, CHEN W, et al.An investigation of rotor aeroacoustics with unsteady motions and uncertainty factors[J][J].Journal of Fluid Mechanics, 2023, 956:A16-
[6]ANOBILE A, BERNARDINI G, TESTA C, et al.Synthesis of a rotor BVI noise active controller through an efficient aerodynamics/aeroacoustics solver[C]//20th AIAA/CEAS Aeroacoustics Conference. 2014: 3186.
[7]HE C, ZHAO J.Modeling rotor wake dynamics with viscous vortex particle method[J].AIAA Journal, 2009, 47(4):902-15
[8]CARDITO F, GORI R, SERAFINI J, et al.Space-time accurate finite-state dynamic inflow modeling for aeromechanics of rotorcraft[J]. Aerospace Science and Technology, 2019, 95:105454.
[9]AGARWAL D, LU L, PADFIELD GD, et al.The use of augmented rotor inflow to predict rotorcraft responses in hover and low-speed manoeuvres[J].The Aeronautical Journal, 2022, 126(1301):1168-86
[10]ZHOU X, ZHANG X Y, WANG B, et al.Aerodynamic and structural characteristics of helicopter rotor in circling flight[J].Chinese Journal of Aeronautics, 2023, 36(12):282-
[11]LEE H, SENGUPTA B, ARAGHIZADEH M S, et al.Review of vortex methods for rotor aerodynamics and wake dynamics[J].Advances in Aerodynamics, 2022, 4(1):20-
[12]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):22006-
[13]WANG H L, ZHANG X Y, ZHAO Q J, et al.Aeroelastic characteristics and vibration reduction method of NTBT rotor with TEF technology[J].Chinese Journal of Aeronautics, 2026, 39(2):103690-
[14]CHENG H, GREENGARD L, ROKHLIN V.A fast adaptive multipole algorithm in three dimensions[J].Journal of computational physics, 1999, 155(2):468-98
[15]BERDOWSKI T, WALTHER J, FERREIRA C, et al.Derivation and analysis of the analytical velocity and vortex stretching expressions for anO(NlogN)-FMM [C]//Journal of Physics: Conference Series. IOP Publishing, 2016, 753(8): 082023
[16]WANG L, LIU X, RENEVIER N, et al.Nonlinear aeroelastic modelling for wind turbine blades based on blade element momentum theory and geometrically exact beam theory[J]. Energy, 2014, 76:487-501.
[17]WU J, MA Y, WANG Z, et al.Structurally coupled characteristics of rotor blade using new rigid-flexible dynamic model based on geometrically exact formulation[J].Chinese Journal of Aeronautics, 2022, 35(6):186-97
[18]WANG Q, ZHAO Q J.Modification of Leishman–Beddoes model incorporating with a new trailing-edge vortex model[J].Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2014, 229(9):1606-15
[19]YANG T, DING Y, CHEN X, et al.Numerical investigation on the blade vortex interaction noise reduction using higher harmonic control[J]. Aerospace Science and Technology, 2024, 155:109609.
[20]LOWSON M, OLLERHEAD J.A theoretical study of helicopter rotor noise[J].Journal of Sound Vibration, 1969, 9(2):197-222
[21]BOXWELL D, SCHMITZ F, SPLETTSTOESSER W, et al.Helicopter model rotor‐blade vortex interaction impulsive noise: scalability and parametric variations[J].Journal of the American Helicopter Society, 1987, 32(1):3-12
[22]YIN J, VAN DER WALL B G, OERLEMANS S.Representative test results from HELINOVI aeroacoustic main rotor/tail rotor/fuselage test in DNW[J]. 2005.
[23]SINGH P, FRIEDMANN P P.Application of vortex methods to coaxial rotor wake and load calculations in hover[J].Journal of Aircraft, 2018, 55(1):373-81
[24]王鑫, 张夏阳, 招启军, 等.基于耦合方法的旋翼悬停状态总距突增气弹载荷分析[J].航空学报, 2025, 46(16):175-191
[25]WANG X, ZHANG X Y, ZHAO Q J, et al.Analysis of the aeroelastic loads of rotor during collective pitch ramp increase in hovering state based on VVPMGEBT coupling method[J].Chinese Journal of Aeronautics, 2025, 46(16):175-191
[26]WILLIAMSON J H.Low-storage runge-kutta schemes[J].Journal of Computational Physics, 1980, 35(1):48-56
[27]王鑫, 张夏阳, 郑礼雄, 等.旋翼高效/高精度气弹全耦合分析方法研究[J/OL]. 航空学报 2026:1-11.
[28]WANG X, ZHANG X Y, ZHENG L X, et al.Research on high-efficiency and high-precision aeroelastic full coupling method of rotor[J/OL]. Chinese Journal of Aeronautics, 2026:1-11. (in Chinese)
[29]SHANG L N, XIA P Q, ZHANG J, et al.Geometrically exact aeroelastic stability analysis of helicopter composite rotor blades in forward flight[J]. Aerospace Science and Technology, 2024, 144:108818.
[30]WANG W Q, CHEN X, YANG T, et al.Numerical research on the rotor “super bladevortex interaction noise” generation mechanism in helicopter roll maneuver state[J].Physics of Fluids, 2025, 37(1):017162-
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