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旋翼/机翼气动干扰对复合式直升机性能影响

杨克龙 韩东

杨克龙,韩东. 旋翼/机翼气动干扰对复合式直升机性能影响[J]. 北京航空航天大学学报,2023,49(7):1761-1771 doi: 10.13700/j.bh.1001-5965.2021.0561
引用本文: 杨克龙,韩东. 旋翼/机翼气动干扰对复合式直升机性能影响[J]. 北京航空航天大学学报,2023,49(7):1761-1771 doi: 10.13700/j.bh.1001-5965.2021.0561
YANG K L,HAN D. Influence of rotor/wing aerodynamic interference on performance of compound helicopters[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(7):1761-1771 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0561
Citation: YANG K L,HAN D. Influence of rotor/wing aerodynamic interference on performance of compound helicopters[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(7):1761-1771 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0561

旋翼/机翼气动干扰对复合式直升机性能影响

doi: 10.13700/j.bh.1001-5965.2021.0561
基金项目: 国家自然科学基金(11972181);直升机旋翼动力学国家级重点实验室基金(2005RAL20200104)
详细信息
    通讯作者:

    E-mail:donghan@nuaa.edu.cn

  • 中图分类号: V211.52

Influence of rotor/wing aerodynamic interference on performance of compound helicopters

Funds: National Natural Science Foundation of China (11972181); Foundation of Rotorcraft Aeromechanics Laboratory (2005RAL20200104)
More Information
  • 摘要:

    为研究旋翼/机翼气动干扰对双螺旋桨推进复合式直升机的高速飞行性能的影响,建立一种可快速预测复合式直升机飞行性能的模型,以加装机翼和螺旋桨的AS365N“海豚”直升机为样例,分析了400 km/h高速飞行时,旋翼/机翼气动干扰对全机飞行性能的影响及机理,并探讨了用副翼操纵配平气动干扰引起的机翼滚转力矩时,全机功率的变化规律。研究表明:气动干扰增加了机翼的诱导速度,导致机翼的升力系数降低、阻力系数增加。在旋翼不对称涡系的作用下,位于旋翼前行侧下机翼的诱导速度和升阻力系数变化比后行侧的更显著。气动干扰导致机翼升力分配从80.00%降低至71.59%,旋翼升力分配从20.04%增加至28.48%。旋翼、螺旋桨和全机功率分别增加了16.60%、1.86%和3.76%。气动干扰使机翼滚转力矩增加、旋翼滚转力矩减小,利于全机配平,但会增加全机功率。用副翼操纵来平衡由气动干扰引起的机翼滚转力矩时,旋翼侧向周期变距和阻力减小,降低了全机功率。

     

  • 图 1  尾迹在旋翼桨尖平面中的示意图

    Figure 1.  Schematic of wake geometry in tip path plane of main rotor

    图 2  涡线对任意点诱导速度

    Figure 2.  Induced velocity at an arbitrary point by vortex filament

    图 3  机翼涡格示意图

    Figure 3.  Schematic of vortex lattice of wing

    图 4  螺旋桨桨叶叶素气动力

    Figure 4.  Aerodynamics of blade element of propeller

    图 5  复合式直升机受力和力矩

    Figure 5.  Forces and moments acting on compound helicopter

    图 6  HV−ID直升机旋翼尾迹形状预测值、试验值和自由尾迹预测值

    Figure 6.  Wake geometry of HV−ID helicopter main roctor among prediction, experimental value and free wake prediction

    图 7  旋翼尾迹诱导速度预测值与试验值

    Figure 7.  Induced velocity among of main roctor prediction, experimental value and free wake prediction

    图 8  机翼升力系数的预测值、试验值和算例值

    Figure 8.  Wing lift coefficient among prediction, experimental value and calculation example

    图 9  螺旋桨拉力系数和效率的预测值与试验值

    Figure 9.  Wing lift coefficient among prediction, experimental value and calculation example

    图 10  机翼剖面(翼型)的诱导速度和升阻力系数沿翼展分布

    Figure 10.  Distribution of induced velocity, lift and drag coefficients of wing sections (airfoils) along wingspan

    图 11  气动干扰对旋翼和机翼的升力分配及滚转力矩的影响

    Figure 11.  Effect of aerodynamic interference on the lift share and rolling moment of main rotor and wing

    图 12  气动干扰对旋翼、螺旋桨和全机功率的影响

    Figure 12.  Effect of aerodynamic interference on the power of main rotor propeller and aircraft

    图 13  功率和功率增加率对比

    Figure 13.  Comparison of power and power increase ratio

    图 14  功率、侧向周期变距和阻力系数对比

    Figure 14.  Comparison of power, cyclic pitch angle and drag coefficient

    表  1  样例复合式直升机参数

    Table  1.   Parameters of a compound helicopter

    部件半径/展长/m平均弦长/m转速/(rad·s−1)负扭/(°)安装角/(°)翼型桨叶片数/机翼展弦比
    旋翼5.97 0.38537.7−10OA212/2095
    机翼8.481.2504NACA65-216.78
    平尾4.0 0.900NACA65-2106.78
    螺旋桨1.350.25157.1−35−10Clark Y5
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-09-18
  • 录用日期:  2022-01-07
  • 网络出版日期:  2022-01-26
  • 整期出版日期:  2023-07-31

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