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共轴刚性旋翼直升机旋翼控制相位角问题分析

袁野 陈仁良 李攀 鲁可

袁野, 陈仁良, 李攀, 等 . 共轴刚性旋翼直升机旋翼控制相位角问题分析[J]. 北京航空航天大学学报, 2017, 43(10): 2047-2053. doi: 10.13700/j.bh.1001-5965.2016.0812
引用本文: 袁野, 陈仁良, 李攀, 等 . 共轴刚性旋翼直升机旋翼控制相位角问题分析[J]. 北京航空航天大学学报, 2017, 43(10): 2047-2053. doi: 10.13700/j.bh.1001-5965.2016.0812
YUAN Ye, CHEN Renliang, LI Pan, et al. Rotor control phase angle analysis for coaxial rigid rotor helicopter[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(10): 2047-2053. doi: 10.13700/j.bh.1001-5965.2016.0812(in Chinese)
Citation: YUAN Ye, CHEN Renliang, LI Pan, et al. Rotor control phase angle analysis for coaxial rigid rotor helicopter[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(10): 2047-2053. doi: 10.13700/j.bh.1001-5965.2016.0812(in Chinese)

共轴刚性旋翼直升机旋翼控制相位角问题分析

doi: 10.13700/j.bh.1001-5965.2016.0812
基金项目: 

国家自然科学基金 51405227

航空科学基金 20145752034

江苏高校优势学科建设工程资助项目 BBBB

详细信息
    作者简介:

    袁野  男, 博士研究生。主要研究方向:直升机飞行动力学

    陈仁良  男, 博士, 教授, 博士生导师。主要研究方向:直升机飞行动力学、直升机空气动力学

    通讯作者:

    陈仁良, E-mail: crlae@nuaa.edu.cn

  • 中图分类号: V212.4

Rotor control phase angle analysis for coaxial rigid rotor helicopter

Funds: 

National Natural Science Foundation of China 51405227

Aeronautical Science Foundation of China 20145752034

the Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions BBBB

More Information
  • 摘要:

    利用共轴刚性旋翼直升机飞行动力学模型,以XH-59A共轴刚性旋翼直升机为研究对象,分析了旋翼控制相位角对纵向配平特性、需用功率以及上、下旋翼桨毂弯矩的影响。基于分析结果,提出了一种针对共轴刚性旋翼直升机的旋翼控制相位角的配置方法。该配置方法以降低直升机需用功率为目标,并保证上、下旋翼桨毂弯矩和配平特性满足要求。通过该方法能使XH-59A直升机在0~80 m/s的飞行速度范围内满足上、下旋翼最大桨毂弯矩和纵向操纵限幅的要求,并且能最多降低8%的直升机需用功率,为共轴刚性旋翼直升机的设计提供了参考依据。

     

  • 图 1  共轴刚性旋翼纵向周期变距操纵挥舞

    Figure 1.  Control flapping of longitudinal cyclic pitch on coaxial rigid rotor

    图 2  稳定平飞时的纵向周期变距

    Figure 2.  Longitudinal cyclic pitch in steady level flight

    图 3  稳定平飞时的俯仰姿态

    Figure 3.  Pitch attitude in steady level flight

    图 4  稳定平飞时的需用功率

    Figure 4.  Power required in steady level flight

    图 5  稳定平飞时的上、下旋翼最大桨毂弯矩

    Figure 5.  Maximum hub bending moment of upper and lower rotor in steady level flight

    图 6  旋翼控制相位角配置流程图

    Figure 6.  Flowchart of rotor control phase angle allocation

    图 7  旋翼控制相位角配置结果

    Figure 7.  Results of rotor control phase angle allocation

    表  1  XH-59A共轴刚性旋翼直升机参数[15]

    Table  1.   Parameters of XH-59A coaxial rigid rotor helicopter[15]

    参数 数值
    旋翼半径/m 5.5
    桨叶片数 3×2
    预扭角/(°) -10
    旋翼速度/(rad·s-1) 36.1
    桨叶根梢比 2
    一阶挥舞固有频率 1.4Ω
    上、下旋翼轴间距/m 0.77
    平尾面积/m2 5.57
    垂尾面积/m2 2.79
    起飞重量/kg 5 500
    下旋翼坐标/m (0, 0, -0.89)
    重心坐标/m (0, 0, 0)
    平尾坐标/m (-6.80, 0, 0.20)
    垂尾坐标/m (-6.80, 0, -0.50)
    下载: 导出CSV
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出版历程
  • 收稿日期:  2016-10-19
  • 录用日期:  2016-11-25
  • 刊出日期:  2017-10-20

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