倾转四旋翼机在典型飞行模式存在多涡系、多部件气动干扰，并引起复杂的非定常噪声特性。为获得直升机模式和固定翼模式综合的高效低噪旋翼外形，分别建立了考虑全机气动环境的旋翼气动和噪声计算方法，开展了桨尖外形参数对旋翼气动和噪声特性的敏感性分析，基于改进的拉丁超立方方法和遗传算法建立了前、后旋翼高效率/低噪外形设计优化方法；通过优化设计获得了一套高效低噪前、后旋翼外形方案，并与基准旋翼的气动、噪声特性进行对比。结果表明，旋翼气动和噪声特性对部分桨尖外形参数较为敏感，能分别对悬停效率和巡航效率造成一定影响。采用本文优化方法后，直升机模式下，前旋翼的悬停效率最大提升1.5%、后旋翼最大提升1.0%，机身水平范围内噪声声压级最大降低1.8db；固定翼模式下，前旋翼的巡航效率提升10.3%，后旋翼提升8.9%，在机身水平范围内噪声声压级最大降低2.2db。
There are multi-vortex and multi-component aerodynamic interference in the tilt-rotor aircraft, which causes complex unsteady noise characteristics. In order to obtain the high-efficiency and low-noise rotor shape combined with helicopter mode and fixed-wing mode, the computation methods of rotor aerodynamic and noise considering the aerodynamic environment of the whole aircraft are established, respectively. The sensitivity analysis of the tip shape parameters to the aerodynamic and noise characteristics of the rotor is carried out. Based on the improved Latin hypercube method and the genetic algorithm, the high-efficiency/low-noise shape design optimization process of the front and rear rotors is established. A set of high-efficiency and low-noise front and rear rotor shapes are obtained, which are further compared with the reference ones. The results show that the aerodynamic and noise characteristics of the rotor are sensitive to the blade tip shape, which can affect the hover efficiency and cruise efficiency severely. After optimization, the hovering efficiencies of the front rotor and rear rotor are increased by 1.5 % and 1.0 %, and the noise pressure level is reduced by 1.8 db. In the fixed-wing mode, the cruise efficiencies of the front rotor and the rear rotor are increased by 10.3 % and 8.9 %, and the noise pressure level is reduced by 2.2 db.
[1]ZHOU P, CHEN R, YUAN Y, et al.Aerodynamic Interference on Trim Characteristics of Quad-Tiltrotor Aircraft[J].Aerospace, 2022, 9(5):262-283
[2]JOANNE L.Optimization methods applied to the aerodynamic design of helicopter rotor blades[J].Journal of the American Helicopter Society, 1987, 32(4):39-44
[3]LIM J W, CHOPRA I.Aeroelastic optimization of a helicopter rotor[D]. Maryland: University of Maryland, 1988.
[4]薛立鹏, 张呈林.倾转旋翼气动优化设计[J].空气动力学学报, 2011, 29(04):453-458
[6]YEO H, JOHNSON W.Aeromechanics analysis of a heavy lift slowed-rotor compound helicopter[J].Journal of Aircraft, 2007, 44(2):501-508
[7]STAHLHUT C.Aerodynamic design optimization of proprotors for convertible-rotor concepts[D]. Maryland: University of Maryland, 2012.
[8]SPIVEY W, MOREHOUSE G.New Insights into the Design of Swept-tip Rotor Blades[D]. The 24th Annual National Forum of the American Helicopter Society, 1970.
[9]SPIVEY R F.Blade Tip Aerodynamics-profile and Planform Effects[R]. Preprint, 1968, 205.
[10]MULLER R.The Influence of Winglets on Rotor Aerodynamics[J].Vertica, 1987, 11(4):601-618
[11]MULLER R.Special Vortices at a Helicopter Rotor Blade[J].Journal of the American Helicopter Society, 1990, 35(4):16-22
[12]BROCKLEHURST A, BARAKOS G N.A review of helicopter rotor blade tip shapes[J]. Progress in Aerospace Sciences, 2013, 56: 35-74
[13]SRINIVAS V, CHOPRA I, Nixon M W.Aeroelastic Analysis of Advanced Geometry Tiltrotor Aircraft[J].Journal of the American Helicopter Society, 1998, 43(3):212-221
[14]VU N A, LEE J W, KIM S, et al.Automated generation of aerofoil characteristics for rotorcraft application[J].Aircraft Engineering, 2012, 84(4):221-230
[15]薛立鹏, 张呈林.倾转旋翼气动优化设计[J].空气动力学学报, 2011, 29(04):453-458
[17]招启军, 蒋霜, 李鹏等.基于方法的倾转旋翼螺旋桨气动优化分析[J].空气动力学学报, 2017, 35(04):544-553
[19]LEE R.Simulation of an isolated tiltrotor in hover with an unstructured overset-grid RANS solver[C]//American Helicopter Society 65th Annual Forum. Grapevine. TX: Annual forum proceedings, 2009: 1182-1200
[20]CASALINO D.Numerical analysis of noise scattering effects due to the airframe in tilt rotor systems [C]//Collection of Technical Papers -12th AIAA/CEAS Aeroacoustics Conference. Cambridge, Massachusetts: AIAA, 2006: 2694-2705
[21]BURLEY C L.MARCOLINI M A. BROOKS T F, et al. Tiltrotor Aeroacoustic Code (TRAC) Predictions and Comparison with Measurements[C]// American Helicopter Society 52th Annual Forum and Technology Display. Washington, D.C: Journal of the American Helicopter Society, 1996: 80-89
[22]BURLEY C L, BROOKS T F, MCCLUER M.Tiltrotor Aeroacoustic Code (TRAC) Prediction Assessment and Initial Comparisons With Tram Test Data[C]//25th European Rotorcraft Forum. Rome, Italy, 1995: 13-22
[23]PRICHARD D S.Initial tiltrotor aeroacoustie code (TRAC) predictions for the XV-15 fight vehicle and comparison with flight measurements[C]//American Helicopter Society $6th Annual Forum, Virginia Beach, 2000: 2-9
[24]LEFEBVRE T, BEAUMIER P, CANARD S.Aerodynamic and aero-acoustie opimization of modem tilt-rotor blades within the ADYN project[C]//4th European Congress on Computational Methods in Applied Sciences and Engineering. Jyvaskyla，2004: 12-18
[25]袁明川, 李尚斌, 江露生等.悬停状态倾转旋翼噪声试验及数值计算[J]. 航空动力学报. 2021, 36(03): 520-529
[27]马锦超, 陆洋, 王亮权, 等.基于高阶谐波控制的倾转旋翼近场气动噪声主动控制试验[J].航空学报, 2024, 45(09):237-247
[29]DUMONT A, LE P A, PETER J, et al.Aerodynamic shape optimization of hovering rotors using a discrete adjoint of the Reynolds-averaged Navier-stokes equations[J].Journal of the American Helicopter Society, 2011, 53(3):1-11
[30]王博, 招启军, 徐国华.悬停状态直升机桨叶扭转分布的优化数值计算[J].航空学报, 2012, 33(07):1163-1172
[32]LI P, ZHAO Q J.CFD calculations on the unsteady aerodynamic characteristics of a tilt-rotor in a conversion mode[J].Chinese Journal of Aeronautics, 2015, 28(6):1593-1605
[33]LEPAPE A.Optimization of helicopter rotor aerodynamic performance in hover[J].Aerospace Science and Technology, 2005, 9(3):191-201
[34]POTSDAM M A.STRAWN R CCFD simulations of tiltrotor configurations in hover[J].Journal of the American Helicopter Society, 2005, 50(1):82-94
[35]张夏阳, 罗彬, 招启军, 等.倾转四旋翼机多涡系气动干扰非定常特性[J/OL]. 航空动力学报, 2024, 1-16[2025-03-04]. https://doi.org/10.13224/j.cnki.jasp.202406.DOI:10.13224/j.cnki.jasp.20240216.
[37]JOHNSON W.Influence of wake models on calculated tiltrotor aerodynamics[D]. Acoustics and Test and Evaluation Specialists' Meeting, 2001: 12-24.
[38]LEISHMAN J G.Principles of Helicopter Aerodynamics[M]. Cambridge: Cambridge Univ Pr, 2006: 23-45.
[39]BATES S.J, SIENZ J, TOROPOV V, et al. Formulation of the Optimal Latin Hypercube Design of Experiments Using a Permutation Genetic Algorithm: AIAA 2004-2011[R]. Palm Springs, California: AIAA, 2004.
CJA