一种倾转涵道螺旋桨的综合设计方法

陈炜锋; 俞志明; 钟伯文; 沈亮; 杨昌发

doi:10.13224/j.cnki.jasp.20221000

一种倾转涵道螺旋桨的综合设计方法

doi: 10.13224/j.cnki.jasp.20221000

陈炜锋^{1, 2,},
俞志明^{1, 2},
钟伯文^{1, 2,*, ,},
沈亮³,
杨昌发³

1.
南昌航空大学飞行器工程学院，南昌 330063
2.
南昌航空大学江西省飞行器设计与气动仿真重点实验室，南昌 330063
3.
江西航空研究院，南昌 330038

详细信息

作者简介:
陈炜锋（1995-），男，硕士生，主要研究方向为飞行器总体与气动设计。E-mail：957323683@qq.com

通讯作者:
钟伯文（1963-），男，研究员，博士，主要研究方向为飞行器总体与气动设计。E-mail：zhongbowen@nchu.edu.cn

中图分类号: V211
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- 文章访问数: 9
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- 被引次数: 0
出版历程
- 收稿日期: 2022-12-31
- 网络出版日期: 2024-05-24

Comprehensive design method for tilting ducted propeller

CHEN Weifeng^{1, 2
,},
YU Zhiming^{1, 2},
ZHONG Bowen^{1, 2,*
, ,},
SHEN Liang³,
YANG Changfa³

1.
School of Aircraft Engineering，Nanchang Hangkong University，Nanchang 330063，China
2.
Jiangxi Key Laboratory of Aircraft Design and Aerodynamic Simulation，Nanchang Hangkong University，Nanchang 330063，China
3.
Jiangxi Aeronautical Research Institute，Nanchang 330038，China

摘要

摘要:
为设计在满足悬停、前飞工况要求的前提下均具有较高的巡航效率和更长的航时的无人机（UAV）倾转涵道螺旋桨，提出了一种倾转涵道螺旋桨的设计及优化方法。该方法基于叶素动量理论、涵道螺旋桨的涡流理论对桨叶进行快速设计，通过计算流体动力学（CFD）修正与迭代两次即可得到满足设计要求的桨叶，并通过综合悬停、前飞两点优化设计得到最终的倾转涵道螺旋桨。设计结果表明：在满足悬停、前飞两个工况的设计要求的前提下，螺旋桨的巡航效率提升至92.3%，航时增加7.1%。该方法设计精度高且能够分别以悬停、前飞为最优设计点进行设计，并对两点综合考虑，使其效率、航时更大化。该方法设计的倾转涵道螺旋桨能够满足巡航效率与航时要求。
- 倾转涵道螺旋桨设计 /
- 涵道螺旋桨的涡流理论 /
- 耦合CFD设计 /
- 巡航效率 /
- 航时
Abstract:
In order to design the tilting ducted propeller of unmanned aerial vehicle (UAV) with higher cruising efficiency and longer flight time on the premise of meeting the requirements of hovering and forward flight, a design and optimization method of tilting ducted propeller was proposed. According to this method, the blade was designed firstly by the classical method using the blade element momentum theory and the vortex theory of the ducted propeller. The blade meeting the design requirements can be obtained through computational fluid dynamics (CFD) correction and the classical method was iterated, and the final tilting ducted propeller was obtained through the iterative and comprehensive optimization design in hover and forward flight states. The design results showed that under the premise of meeting the design requirements of hovering and forward flight, the cruising efficiency of the UAV was increased to 92.3%, and the flight endurance was increased by 7.1%. This method can achieve high design accuracy and can be designed with hover and forward flight as the optimal design points, and the two optimal design points were considered comprehensively to increase the UAV’s cruising efficiency and flight time. The tilting ducted propeller designed by this method can meet the requirements on the UAV’s cruising efficiency and flight endurance.
- design of tilting ducted propeller /
- vortex theory of ducted propeller /
- coupled CFD design /
- cruising efficiency /
- flight time

HTML

图 1 叶素受力示意图

Figure 1. Schematic diagram of propeller element force

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图 2 几何模型图

Figure 2. Diagram of geometric model

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图 3 涵道螺旋桨计算网格

Figure 3. Computational mesh of ducted propeller

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图 4 桨叶局部网格示意图

Figure 4. Schematic diagram of local mesh of propeller blade

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图 5 不同翼型的升阻系数比较图

Figure 5. Comparison of lift drag coefficients of different airfoils

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图 6 弦长与扭转角设计结果

Figure 6. Design results of chord length and twist angle

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图 7 修正后的弦长与扭转角设计结果

Figure 7. Modified design results of chord length and twist angle

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图 8 弦长与扭转角设计结果

Figure 8. Design results of chord length and twist angle

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图 9 修正后的弦长与扭转角设计结果

Figure 9. Modified design results of chord length and twist angle

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图 10 设计流程图

Figure 10. Design flow chat

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图 11 不同权值对应的悬停-前飞功率

Figure 11. Hover-forward flight power corresponding to different weights

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图 12 不同权值对应的总续航时间

Figure 12. Total flight duration corresponding to different weights

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Figure 13. Comprehensive design results of chord length and twist angle

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图 14 综合设计之后的涵道螺旋桨几何模型

Figure 14. Duct propeller geometry model after integrated design

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图 15 涵道螺旋桨倾角与拉力关系图

Figure 15. Relationship between inclination angle and pulling force of ducted propeller

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图 16 涵道螺旋桨倾角与升力关系图

Figure 16. Diagram of relationship between inclination angle and lift of ducted propeller

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表 1 计算结果与试验结果对比

Table 1. Comparison between calculation results and test results

参数	计算结果		试验结果
参数	1355万网格	2841万网格	试验结果
桨叶拉力系数	0.1756	0.1760	0.1890
扭矩系数	0.0278	0.0281	0.0298
涵道拉力占比	0.557	0.559	0.571

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表 2 涵道螺旋桨设计值与计算值结果对比

Table 2. Comparison between design value and calculated value of ducted propeller

参数	设计值	CFD计算值	误差/%
桨叶拉力/N	121.230	160.000	24.2
扭矩/（N·m）	13.240	12.500	5.6
总拉力/N	325.000	336.160	3.4
功率/W	5293.705	4997.313	5.6
功率载荷/（kg/kW）	6.141	6.722	9.4
涵道拉力占比	0.373	0.520	39.4

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表 3 修正后的涵道螺旋桨设计值与计算值结果对比

Table 3. Comparison between design value and calculated value of modified ducted propeller

参数	设计值	CFD计算值	误差/%
桨叶拉力/N	156.000	148.690	4.7
扭矩/（N·m）	11.380	11.700	2.8
总拉力/N	325.000	325.756	0.2
功率/W	4550.027	4677.972	2.8
功率载荷/（kg/kW）	7.143	6.963	2.5
涵道拉力占比	0.520	0.544	4.6

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表 4 设计状态一条件下的前飞数据

Table 4. Forward flight data under the first condition of design state

转速/（r/min）	总拉力/N	功率/W	效率
4400	47.575	2429.682	0.817
4600	68.852	3408.736	0.842
4700	80.006	3930.843	0.849
4750	82.721	4200.213	0.851
4800	91.508	4475.329	0.853
5000	115.521	5634.207	0.855
5200	140.896	6881.925	0.854

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表 5 涵道螺旋桨设计值与计算值结果对比

Table 5. Comparison between design value and calculated value of ducted propeller

参数	设计值	CFD计算值	误差/%
桨叶拉力/N	77.900	76.982	1.2
扭矩/（N·m）	10.612	10.637	0.2
总拉力/N	82.000	84.469	3.0
功率/W	4242.961	4252.956	0.2
功率载荷/（kg/kW）	1.933	1.987	2.8
涵道拉力占比	0.050	0.089	78

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表 6 修正后的涵道螺旋桨设计值与计算值结果对比

Table 6. Comparison between design value and calculated value of modified ducted propeller

参数	设计值	CFD计算值	误差/%
桨叶拉力/N	72.160	71.800	0.5
扭矩/（N·m）	9.216	9.245	0.3
总拉力/N	82.000	82.434	0.6
功率/W	3687.000	3698.23	0.3
功率载荷/（kg/kW）	2.224	2.228	0.2
涵道拉力占比	0.120	0.129	7.5

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表 7 设计状态二条件下的悬停数据

Table 7. Hover data under the second condition of design state

转速/（r/min）	总拉力/N	功率/W
4000	185.863	5149.603
5000	241.681	9435.721
5500	277.366	12434.458
5800	304.904	16451.568
6000	325.278	18086.135

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表 8 两设计状态的悬停功率和前飞功率

Table 8. Hover and front flying power meter in two design states

参数	设计状态一	设计状态二
悬停功率/W	4678	18086
前飞功率/W	4200	3696

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表 9 涵道螺旋桨悬停和前飞数值计算结果

Table 9. Numerical calculation results of ducted propeller hovering and forward flight

参数	悬停	前飞
桨叶拉力/N	152.521	72.803
扭矩/（N·m）	12.794	7.347
总拉力/N	325.102	82.154
功率/W	5111.589	3705.878
功率载荷/（kg/kW）	6.3610	2.217
效率		0.923

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