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首页 > 过刊浏览>2023年第55卷第4期 >658-666. DOI:10.16356/j.1005-2615.2023.04.011
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多涵道无人机设计及悬停性能数值仿真
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作者:
作者单位:

南京航空航天大学能源与动力学院，南京 210016

通讯作者:

王志强，男，博士，副教授，E-mail：wangzq1981@126.com。

中图分类号:

V279.2

基金项目:

基础加强计划技术领域基金（2021-JCJQ-JJ-0785）。


Design of Multi-ducted UAV and Its Numerical Simulation on Hover Performance
Author:
Affiliation:

College of Energy and Power Engineering，Nanjing University of Aeronautics & Astronautics，Nanjing 210016，China

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    摘要:

    针对无人机空中自主对接和组合飞行任务需求设计了6涵道螺旋桨无人机气动构型。运用数值模拟对该型无人机进行悬停工况气动特性研究，研究不同悬停转速下整机气动性能的变化，并在涵道环括工况下对螺旋桨进行气动优化。研究结果表明：螺旋桨是悬停升力的主要来源，随着转速变化，涵道升力始终占总升力的17%左右；阻力来自机体上表面和电机支架的迎风阻力，支架的阻力达到涵道螺旋桨总升力的10%；随着桨盘载荷提升，无人机功率载荷降低；涵道的存在影响了螺旋桨的滑流特性，造成桨盘平面轴向速度增加，截面翼型迎角变小，工作效率降低，经过合理调整其扭转角分布螺旋桨效率得到提升，拉力提高3.3%，效率提高2.9%。

    Abstract:

    In order to meet the requirements of autonomous docking and combined flight of unmanned aerial vehicles （UAVs）， the aerodynamic configuration of six-ducted UAV was designed. The aerodynamic characteristics of the UAV in hover condition were studied by numerical simulation， the aerodynamic performance changes of the whole machine under different propeller speeds were studied， and the aerodynamic optimization of the propeller was carried out under the duct condition. The results show that the propeller is the main source of hover lift， and with the change of rotation speed， the lift force of the duct always accounts for about 17% of the total lift force. The resistance comes from the upper surface of the vehicle and the motor support， which reaches 10% of the total lift of the UAV. With the increase of the propeller plate load， the power load of UAV decreases. The presence of the duct affects the slip flow characteristics of the propeller， resulting in the increase of the axial speed of the propeller disc， the decrease of the angle of attack of the section airfoil， and the decrease of the working efficiency. By adjusting the distribution of the torsion angle， the propeller efficiency is improved， the lift is increased by 3.3%， and the efficiency is increased by 2.9%.

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柳莳春,王志强,李传鹏,屠宝锋.多涵道无人机设计及悬停性能数值仿真[J].南京航空航天大学学报,2023,55(4):658-666

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  • 收稿日期:2022-11-10
  • 最后修改日期:2023-01-12
  • 在线发布日期: 2023-08-05
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