混合动力分布式电推进飞行器总体设计

李嘉诚; 盛汉霖; 陈欣; 史昊蓝; 张天宏

doi:10.13224/j.cnki.jasp.20220693

混合动力分布式电推进飞行器总体设计

doi: 10.13224/j.cnki.jasp.20220693

南京航空航天大学能源与动力学院，南京 210016

基金项目: 国家自然科学基金（51906103 ，52176009）

详细信息

作者简介:
李嘉诚（1995-），男，博士生，研究方向为飞行/推进一体化控制领域

通讯作者:
盛汉霖（1986-），男，教授、博士生导师，博士，研究方向为航空发动机控制领域。E-mail：dreamshl@nuaa.edu.cn

中图分类号: V236
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- 被引次数: 0
出版历程
- 收稿日期: 2022-09-15
- 网络出版日期: 2023-11-27

System design of hybrid distributed electric propulsion aircraft

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

摘要

摘要:
以运-7飞机作为参考机型，进行了分布式电推进飞行器的总体设计与性能分析。设计了改型后的分布式电推进飞行器的动力系统，包括螺旋桨参数设计，机翼参数修正，电动机功率计算与选型，螺旋桨气动设计，最终完成混合动力系统的设计。完整地计算了改型后飞行器的各部分质量增减情况并分析其飞行性能，相比参考机型，航程与航时分别增加了540 km与1.2 h，增加幅度超过20%，最终进行了分布式电推进飞行器的三维建模与气动特性分析。为分布式电推进飞行器建模、仿真与控制及工程应用提供了理论依据。
- 分布式电推进 /
- 绿色航空 /
- 飞行器设计 /
- 推进系统设计 /
- 性能分析 /
- 气动特性分析
Abstract:
The Y-7 aircraft was used as the reference model to carry out the overall design and performance analysis of the distributed electric propulsion aircraft. The power system of the distributed electric propulsion aircraft was designed, including design of propeller parameters, correction of wing parameters, calculation of motor power and type selection and aerodynamic design of propeller, and finally the design of hybrid power system was completed. The mass increase and decrease of each part of the distributed electric propulsion aircraft were completely calculated and its flight performance was analyzed. Compared with the reference model, the range and duration increased by 540 km and 1.2 h respectively, up by 20%. Finally, the three-dimensional modeling was established and aerodynamic characteristics of the distributed electric propulsion aircraft were analyzed. The result provides a theoretical basis for the modeling, simulation and control of distributed electric propulsion aircraft and its engineering applications.
- distributed electric propulsion /
- green aviation /
- aircraft design /
- propulsion system design /
- performance analysis /
- aerodynamic characteristics analysis

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图 1 运-7运输机

Figure 1. Transport plane Y-7

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图 2 本研究技术路线图

Figure 2. Technology roadmap of this research

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图 3 桨盘前后流体流速的变化

Figure 3. Fluid velocity before and after the propeller disk

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图 4 起飞阶段剖面示意图

Figure 4. Diagrammatic sketch of the takeoff phase

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图 5 起飞场道阶段剖面示意图

Figure 5. Diagrammatic sketch of the takeoff runway phase

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图 6 EMRAX系列电动机

Figure 6. EMRAX series motors

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图 7 螺旋桨三维造型图

Figure 7. Three-dimensional modeling of the propeller

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图 8 计算航程和续航时间的典型飞行剖面

Figure 8. Typical flight profile for calculating range and endurance

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图 9 分布式电推进飞行器三维模型

Figure 9. Three-dimensional model of the distributed electric propulsion aircraft

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图 10 运-7飞机与分布式电推进飞行器机翼对比

Figure 10. Wing comparison between the Y-7 aircraft and the distributed electric propulsion aircraft

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图 11 机身压强分布（空速为125 m/s，迎角为2°）

Figure 11. Pressure distribution of the airframe （airspeed of 125 m/s, angle of attack of 2°）

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图 12 机翼压强分布（空速为125 m/s，迎角为2°）

Figure 12. Pressure distribution of the wing （airspeed of 125 m/s, angle of attack of 2°）

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图 13 垂直尾翼压强分布（空速为125 m/s，侧滑角为0°）

Figure 13. Pressure distribution of the vertical tail （airspeed of 125 m/s, sideslip angle of 0°）

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图 14 水平尾翼压强分布（空速为125 m/s，迎角为2°）

Figure 14. Pressure distribution of the horizontal tail （airspeed of 125 m/s, angle of attack of 2°）

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表 1 参考机型Y-7基本飞行参数

Table 1. Parameters of the reference aircraft Y-7

参数	数值
翼展/m	29.2
展弦比	11.7
机翼面积/m²	74.98
机长/m	23.7
机高/m	8.55
机身宽度/m	2.9
机身高度/m	2.50
空质量/kg	13 300
最大起飞质量/kg	21 800
最大载油量/kg	3 950
最大燃油航程/km	2 400
发动机单台功率/kW	2 050.7
单台发动机质量/kg	481
正常巡航速度/（km/h）	450
着陆速度/（km/h）	165
爬升率/（m/min）	114
起飞滑跑距离/m	600
起飞离地速度/（km/h）	200
螺旋桨直径/m	3.90
螺旋桨转速/（r/min）	1 200

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表 2 EMRAX电动机输出特性

Table 2. Output characteristics of EMRAX motors

参数	型号
参数	188	208	228	268	348
最大可持续输出功率/kW	32	40	55	110	210
峰值功率/kW	60	75	100	230	380
最大可持续输出扭矩/（N·m）	50	80	120	250	500
质量/kg	7.2	9.4	12.3	20.3	40

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表 3 机身气动力随迎角变化

Table 3. Airframe aerodynamic force with the change of angle of attack

迎角/（°）	升力/N	阻力/N
−6	−8730	4473.6
−4	−6083	3788.5
−2	−4125	3311.6
0	−2707	3012.7
2	−1594	2843.5
4	−623	2775.2
6	352	2790.5
8	1578	2905.4
10	3364	3163.8

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表 4 机身气动力随侧滑角变化

Table 4. Airframe aerodynamic force with the change of sideslip angle

侧滑角/（°）	侧向力/N	阻力/N
0	0	3012.7
−2	377	3040.8
−4	877	3125.9
−6	1650	3277.5

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表 5 机翼气动力随迎角变化

Table 5. Wing aerodynamic force with the change of angle of attack

迎角/（°）	升力/N	阻力/N
−6	−152230	6976
−4	−100690	4339
−2	−41807	2777
0	21163	2249
2	85730	2666
4	149850	3837
6	210610	6147
8	263410	9445

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表 6 垂直尾翼气动力随侧滑角变化

Table 6. Vertical tail aerodynamic force with the change of sideslip angle

侧滑角/（°）	侧向力/N	阻力/N
0	0	836
−2	8983	985
−4	18089	1432
−6	27489	2205
−8	37233	3332

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表 7 水平尾翼气动力随迎角变化

Table 7. Horizontal tail aerodynamic force with the change of angle of attack

迎角/（°）	升力/N	阻力/N
−4	−37839	1824.5
−2	−18763	1049.7
0	523.05	803.09
2	19871	1071
4	39175	1873.4
6	58278	3251.9
8	76173	5180.6

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表 8 螺旋桨气动特性

Table 8. Aerodynamic characteristics of propeller

转速/ （r/min）	总距/ （°）	拉力/ N	功率/ kW	尾流速度/ （m/s）	效率/ %
2500	12	380	56.3	127.6	86.1
2500	13	586	82.1	128.7	91.9
2500	14	802	110	129.8	94.6
2500	15	1020	139	131.0	96.1

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