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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

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文章导航 > 北京航空航天大学学报  > 2016 >  42(2): 294-302.
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
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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)
shu

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
  • 1.

    北京航空航天大学机械工程及自动化学院, 北京 100083

  • 2. 沈阳航空航天大学航空航天工程学部, 沈阳 110136

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

  • 1.

    School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • 2. Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China

    摘要
  • 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。

     

    Abstract: A calculation method of blade element aerodynamic loads based on small perturbation theory is established for helicopter flight simulation application. The method synthesizes flap-lag-torsion elastic rotor blade mode, couples rotor dynamic inflow, unsteady aerodynamics model with dynamic stall and rotor trimming model. The entire model is developed in a standard state-space form. To verify this model, the UH-60A helicopter is taken as an example, and the effects of yaw flow on rotor aerodynamic performance are studied at low speed flight and high speed flight. It is shown that yaw flow has a greater effect on rotor aerodynamic performance at high speed flight. Blade induced velocity fields and aerodynamic loads are simulated, and the results are compared with flight test data. It is shown by the results that the method can accurately predict the unsteady aerodynamic rotor loads in steady flight by capturing its variational characteristics along blade azimuthal locations, and it is still applicable for high speed flight.

     

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出版历程
  • 收稿日期:  2015-02-09
  • 网络出版日期:  2016-02-20

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