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基于小扰动理论的桨叶叶素气动载荷计算方法

王巍 李东升 刘春

王巍, 李东升, 刘春等 . 基于小扰动理论的桨叶叶素气动载荷计算方法[J]. 北京航空航天大学学报, 2016, 42(2): 294-302. doi: 10.13700/j.bh.1001-5965.2015.0087
引用本文: 王巍, 李东升, 刘春等 . 基于小扰动理论的桨叶叶素气动载荷计算方法[J]. 北京航空航天大学学报, 2016, 42(2): 294-302. doi: 10.13700/j.bh.1001-5965.2015.0087
WANG Wei, LI Dongsheng, LIU Chunet al. Calculation method of blade element aerodynamic loads based on small perturbation theory[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(2): 294-302. doi: 10.13700/j.bh.1001-5965.2015.0087(in Chinese)
Citation: WANG Wei, LI Dongsheng, LIU Chunet al. Calculation method of blade element aerodynamic loads based on small perturbation theory[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(2): 294-302. doi: 10.13700/j.bh.1001-5965.2015.0087(in Chinese)

基于小扰动理论的桨叶叶素气动载荷计算方法

doi: 10.13700/j.bh.1001-5965.2015.0087
详细信息
    作者简介:

    王巍 女,博士研究生,讲师。主要研究方向:直升机建模技术。Tel.:024-89723447 E-mail:wangwei7832@163.com;刘春 男,博士,教授,博士生导师。主要研究方向:飞行仿真建模技术、虚拟现实。Tel.:024-89723716 E-mail:mr_chun_liu@sina.com

    通讯作者:

    刘春,Tel.:024-89723716 E-mail:mr_chun_liu@sina.com

  • 中图分类号: V211.52

Calculation method of blade element aerodynamic loads based on small perturbation theory

  • 摘要: 针对直升机飞行仿真应用,采用小扰动理论建立了桨叶叶素气动载荷计算方法。该计算方法集成了弹性桨叶挥舞-摆振-扭转模态,耦合了旋翼动态入流、非定常动态失速气动模型和旋翼配平模型。整个算法采用标准的状态空间格式。为验证算法,以UH-60A直升机为例,在低速和高速2种定常飞行情况下,研究了偏航流效应对旋翼气功性能的影响,结果表明高速飞行时偏航流效应对旋翼气功性能影响较大。模拟了桨盘平面诱导速度分布以及桨叶叶素气动载荷,将仿真结果与飞行试验结果进行对比验证,本文建立的方法可以准确地求解定常飞行时桨叶的非定常气动载荷,捕捉其沿方位角的变化特征,对于大速度前飞仍能适用。

     

  • [1] 栗英杰. 直升机飞行模拟器关键技术研究[D].长春:吉林大学,2012:1-2. LI Y J.Research on key technologies of helicopter flight simulator[D].Changchun:Jilin University,2012:1-2(in Chinese).
    [2] 王芳. 机动飞行状态下的旋翼入流和响应分析[D].南京:南京航空航天大学,2007:4-5. WANG F.Investigation on the inflow and aerodynamic response of rotors in maneuvering flight[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2007:4-5(in Chinese).
    [3] PITT D M,PETERS D A.Theoretical prediction of dynamic inflow derivatives[J].Vertica,1981,5(1):21-34.
    [4] PETERS D A,BOYD D D,HE C J.Finite-state induced-flow model for rotors in hover and forward flight[J].Journal of the American Helicopter Society,1989,34(4):5-17.
    [5] KELLER J D. An investigation of helicopter dynamic coupling using an analytical model[J].Journal of the American Helicopter Society,1996,41(4):322-330.
    [6] ZHAO J G. Dynamic wake distortion model for helicopter maneuvering flight[D].Atlanta,Georgia:Georgia Institute of Technology,2005:35-36.
    [7] DUMONT A,LE PAPE A,PETER J.Aerodynamic shape optimization of hovering rotors using a discrete adjoint of the reynolds-averaged navier-stokes equations[J].Journal of the American Helicopter Society,2011,56(3):256-258.
    [8] 徐广,王博,徐国华.基于CFD的直升机旋翼流场及气动力计算[J].南京航空航天大学学报,2011,43(3):369-374. XU G,WANG B,XU G H.Computation on flow field and aerodynamic load of helicopter rotors based on CFD[J].Journal of Nanjing University of Aeronautics & Astronautics,2011,43(3):369-374(in Chinese).
    [9] 李攀. 旋翼非定常自由尾迹及高置信度直升机飞行力学建模研究[D].南京:南京航空航天大学,2010:6-7. LI P.Rotor unsteady free-vortex wake model and investigation on high-fidelity modeling of helicopter flight dynamics[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2010:6-7(in Chinese).
    [10] CURTISS H C. Stability and control modeling[J].Vertica,1988,12(4):381-394.
    [11] TISCHLER M B. System identification requirements for high-bandwidth rotorcraft flight control system design[J].Journal of Guidance,Control,Dynamics,1990,13(5):835-841.
    [12] HOWLETT J J. UH-60 black hawk engineering simulation program:Volume I-mathematical model:NASA CR-166309[R].Reston:AIAA,1981:27-58.
    [13] BHAGWAT M J.Mathematical modeling of the transient dynamics of helicopter rotor wakes using a time-accurate free-vortex methods[D].College Park,Maryland:University of Maryland,2001:97-121.
    [14] RIBERA M. Helicopter flight dynamics simulation with with a time-accurate free-vortex wake model[D].College Park,Mary-land:University of Maryland,2007:104-150.
    [15] 赵景根,徐国华,招启军.基于自由尾迹分析的直升机旋翼下洗流场计算方法[J].兵工学报,2006,27(1):63-68. ZHAO J G,XU G H,ZHAO Q J.A calculating method of helicopter rotor downwash flowfield based on free wake analysis[J].Acta Armamentarii,2006,27(1):63-68(in Chinese).
    [16] LI P,CHEN R L.Rotor unsteady aerodynamics model using an efficient free-vortex method[J].Aircraft Engineering and Aerospace Technology,2012,84(5):311-320.
    [17] 刘勇,邵松,朱清华,等.基于时间精确自由尾迹方法的旋翼非定常气动特性分析[J].航空学报,2012,33(4):607-616. LIU Y,SHAO S,ZHU Q H,et al.Analysis of rotor unsteady aerodynamic characteristics based on time accurate free wake formulation[J].Acta Aeronautica et Astronautica Sinica,2012,33(4):607-616(in Chinese).
    [18] 吕维梁,史勇杰,魏鹏,等.旋翼非定常气动载荷及瞬态气动响应计算[J].南京航空航天大学学报,2013,45(1):21-27. LV W L,SHI Y J,WEI P,et al.Computation of rotor unsteady aerodynamic loads and transient aerodynamic response[J].Journal of Nanjing University of Aeronautics & Astronautics,2013,45(1):21-27(in Chinese).
    [19] 曹义华. 直升机机动飞行旋翼的气动力模拟[J].航空学报,1999,20(1):39-42. CAO Y H.Modeling the aerodynamic forces of a maneuvering helicopter rotor[J].Acta Aeronautica et Astronautica Sinica,1999,20(1):39-42(in Chinese).
    [20] CAO Y H. A new inverse solution technique for studying helicopter maneuvering flight[J].Journal of the American Helicopter society,2000,45(1):43-53.
    [21] 苏媛,曹栋,曹义华.计及大迎角失速的直升机旋翼的气动力模拟[J].北京航空航天大学学报,2010,36(2):168-171. SU Y,CAO D,CAO Y H.Simulation of helicopter rotor aerody-namic force in conditions of high angle of attack and dynamic stall[J].Journal of Beijing University of Aeronautics and Astronautics,2010,36(2):168-171(in Chinese).
    [22] DREIER M E. Introduction to helicopter and tiltrotor flight simulation[M].Reston:AIAA,2007:190-194.
    [23] HOUSEN S S,BROWN R E.Rotor-wake modeling for simulation of helicopter flight mechanics in autorotation[J].Journal of Aircraft,2003,40(5):938-945.
    [24] LI P,CHEN R L.A mathematical model for helicopter comprehensive analysis[J].Chinese Journal of Aeronautics,2010,23(3):320-326.
    [25] Leishman J G,Crouse G L.State-space model for unsteady airfoil behavior and dynamic stall:AIAA-1989-1219[R].Reston:AIAA,1989:36-38.
    [26] 徐进. 直升机大机动飞行中旋翼非定常空气动力研究[D].南京:南京航空航天大学,2007:47-48. XU J.Unsteady aerodynamics investigation for the isolated rotor in large amplitude maneuvering flight[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2007:47-48(in Chinese).
    [27] PURSER P E,SPEARMAN M L.Wind-tunnel tests at low speed of swept and yawed wings having various plan forms:NACA Technical Note 2445[R].Reston:NACA,1951:86-87.
    [28] SITARAMAN J. CFD based unsteady aerodynamic modeling for rotor aeroelastic analysis[D].Maryland:University of Maryland,2003:119,152.
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出版历程
  • 收稿日期:  2015-02-09
  • 刊出日期:  2016-02-20

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