基于无级变速的直升机变旋翼转速控制模拟方法研究
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摘要
为了扩大直升机变旋翼转速变化范围,开展了基于无级变速机构的直升机/传动系统/发动机连续变旋翼转速控制模拟方法研究。基于叶素法和容积动力学方法,建立了主旋翼/发动机综合数学模型用于直升机推进系统仿真,该模型由主旋翼简化模型和涡轴发动机部件级模型组成。在主旋翼/发动机综合模型的基础上,加入了基于能量法建立的无级变速传动装置动力学模型,通过变传动比实现变旋翼转速控制模拟,通过定常来流状态下的数字仿真,分析变旋翼转速控制过程对主旋翼和发动机状态的影响。结果表明,提出的变旋翼转速控制模拟方法在保证涡轴发动机动力涡轮转速变化小于1.5%的前提下使旋翼转速连续变化25%,建立的直升机/传动系统/发动机综合模型为变旋翼转速技术的设计与验证提供了较可靠的数字仿真平台。
In order to expand the narrow range that the main rotor speed varies in,based on an ideal Continuously Variable Transmission model,a method by comprehensive simulation and control of helicopter variable rotor speed with coupled engine and transmission was proposed. Improved comprehensive rotorcraft propulsion system model was composed of a simplified model of main rotor and a component-level model of turbo-shaft engine by blade element analysis and volume dynamics theory. Then a Continuously Variable Transmission model by energy method was appended to the system model,and the rotor speed could be shifted with a variable gear ratio. Finally,the influence on the state of the main rotor and engine in the process of a rotor speed shifting control was analyzed by the numerical simulation. The results show that the rotor speed could be continuously changed up to 25% with only 1.5% change of the power-turbine speed by the above programs,therefore a valuable verification platform is provided herein.
In order to expand the narrow range that the main rotor speed varies in,based on an ideal Continuously Variable Transmission model,a method by comprehensive simulation and control of helicopter variable rotor speed with coupled engine and transmission was proposed. Improved comprehensive rotorcraft propulsion system model was composed of a simplified model of main rotor and a component-level model of turbo-shaft engine by blade element analysis and volume dynamics theory. Then a Continuously Variable Transmission model by energy method was appended to the system model,and the rotor speed could be shifted with a variable gear ratio. Finally,the influence on the state of the main rotor and engine in the process of a rotor speed shifting control was analyzed by the numerical simulation. The results show that the rotor speed could be continuously changed up to 25% with only 1.5% change of the power-turbine speed by the above programs,therefore a valuable verification platform is provided herein.
引文
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[21]Lu Z.Acceleration Simulation of a Vehicle with a Continuously Variable Power Split Transmission[D].West Virginia:West Virginia University,1998.
[22]Veres J P,Henriksen S.Compressor Study to Meet Large Civil Tilt Rotor Engine Requirements[M].Cleveland:National Aeronautics and Space Administration,Glenn Research Center,2009.
[23]Snyder C A,Thurman D R.Gas Turbine Characteristics for a Large Civil Tilt-Rotor(LCTR)[M].Cleveland:National Aeronautics and Space Administration,Glenn Research Center,2010.
[2]Johnson W,Yamauchi G K,Watts M E.NASA Heavy Lift Rotorcraft Systems Investigation[R].SAE Technical,2005-01-3149.
[3]Saribay Z,Lemanski A,Elmoznino M.Pericyclic NonTraction Continuously Variable Speed Transmission(PCVT):Rotorcraft Applications[C].Phoenix,AZ:AHS International 62nd Annual Forum and Technology Display,2006.
[4]Goi T,Kawakami K,Yamakawa E,et al.Variable Rotor Speed Transmission with High Speed Traction Drive[C].Montreal:AHS International Annual Forum,55th,1999:748-759.
[5]Iwata T.Integrated Flight/Propulsion Control with Variable Rotor Speed Command for Rotorcraft[D].California:Stanford University,1996.
[6]Iwata T,Rock S M.Benefits of Variable Rotor Speed in Integrated Helicopter/Engine Control[C].Monterey:AIAA Guidance,Navigation and Control Conference,1993:1342-1348.
[7]Maisal M D,Giulianetti D J,Dugan D C.The History of the XV-15 Tilt Rotor Research Aircraft:From Concept to Flight[R].NASA SP-2000-4517.
[8]Germanowski P J,Stille B L,Strauss M P.Technology Assessment for Large Vertical-Lift Transport Tiltrotors[M].California:National Aeronautics and Space Administration,Ames Research Center,2010.
[9]Blackwell R,Millott T.Dynamics Design Characteristics of the Sikorsky X2 Technology?Demonstrator Aircraft[J].Annual Forum Proceedings-American Helicopter Society,2008,64(1).
[10]Bagai A.Aerodynamic Design of the X2 Technology Demonstrator?Main Rotor Blade[J].Annual Forum Proceedings-American Helicopter Society,2008,64(1).
[11]韩东.变转速旋翼直升机性能及配平研究[J].航空学报,2013,34(6):1241-1248.
[12]姚文荣,涡轴发动机/旋翼综合建模控制及优化研究[D].南京:南京航空航天大学,2008.
[13]姚文荣,孙健国.基于变旋翼转速的涡轴发动机优化控制[J].航空动力学报,2007,22(9):1573-1577.
[14]张海波,姚文荣,陈国强.涡轴发动机/直升机综合控制仿真平台设计[J].推进技术,2011,32(3):383-390.(ZHANG Hai-bo,YAO Wen-rong,CHEN Guoqiang.Design of a Numeric Simulation Platform for Integrated Turbo-Shaft Engine/Helicopter Control System[J].Journal of Propulsion Technology,2011,32(3):383-390.)
[15]Kish J.Vertical Lift Drive System Concept Studies Variable Speed/Two-Speed Transmissions[R].NASA/CR—2002-211564.
[16]陈国强.直升机/发动机实时优化控制规律与硬件平台研究[D].南京:南京航空航天大学,2012.
[17]Mc Cormick B W.Aerodynamics of V/STOL Flight[M].New York:Courier Corporation,1967:347-366.
[18]Houghton E L,Carpenter P W.Aerodynamics for Engineering Students[M].UK:Butterworth-Heinemann,2003:105-125.
[19]Dreier M E.Introduction to Helicopter and Tiltrotor Simulation[M].Reston:AIAA Press,2007:142-145.
[20]Yamamoto M,Wakahara T,Okahara H,et al.Hydraulic System,Shift,and Lockup Clutch Controls Developed for the Large Torque Capacity CVT[C].California:2004 International Continuously Variable and Hybrid Transmission Congress,2004.
[21]Lu Z.Acceleration Simulation of a Vehicle with a Continuously Variable Power Split Transmission[D].West Virginia:West Virginia University,1998.
[22]Veres J P,Henriksen S.Compressor Study to Meet Large Civil Tilt Rotor Engine Requirements[M].Cleveland:National Aeronautics and Space Administration,Glenn Research Center,2009.
[23]Snyder C A,Thurman D R.Gas Turbine Characteristics for a Large Civil Tilt-Rotor(LCTR)[M].Cleveland:National Aeronautics and Space Administration,Glenn Research Center,2010.