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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

李嘉诚, 盛汉霖, 陈欣, 等. 混合动力分布式电推进飞行器总体设计[J]. 航空动力学报, 2024, 39(9):20220693 doi: 10.13224/j.cnki.jasp.20220693
引用本文: 李嘉诚, 盛汉霖, 陈欣, 等. 混合动力分布式电推进飞行器总体设计[J]. 航空动力学报, 2024, 39(9):20220693 doi: 10.13224/j.cnki.jasp.20220693
LI Jiacheng, SHENG Hanlin, CHEN Xin, et al. System design of hybrid distributed electric propulsion aircraft[J]. Journal of Aerospace Power, 2024, 39(9):20220693 doi: 10.13224/j.cnki.jasp.20220693
Citation: LI Jiacheng, SHENG Hanlin, CHEN Xin, et al. System design of hybrid distributed electric propulsion aircraft[J]. Journal of Aerospace Power, 2024, 39(9):20220693 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
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

System design of hybrid distributed electric propulsion aircraft

  • 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。

     

  • 图 1  运-7运输机

    Figure 1.  Transport plane Y-7

    图 2  本研究技术路线图

    Figure 2.  Technology roadmap of this research

    图 3  桨盘前后流体流速的变化

    Figure 3.  Fluid velocity before and after the propeller disk

    图 4  起飞阶段剖面示意图

    Figure 4.  Diagrammatic sketch of the takeoff phase

    图 5  起飞场道阶段剖面示意图

    Figure 5.  Diagrammatic sketch of the takeoff runway phase

    图 6  EMRAX系列电动机

    Figure 6.  EMRAX series motors

    图 7  螺旋桨三维造型图

    Figure 7.  Three-dimensional modeling of the propeller

    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

    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

    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

    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°)

    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°)

    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°)

    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°)

    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/m29.2
    展弦比11.7
    机翼面积/m274.98
    机长/m23.7
    机高/m8.55
    机身宽度/m2.9
    机身高度/m2.50
    空质量/kg13 300
    最大起飞质量/kg21 800
    最大载油量/kg3 950
    最大燃油航程/km2 400
    发动机单台功率/kW2 050.7
    单台发动机质量/kg481
    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/m600
    起飞离地速度/(km/h)200
    螺旋桨直径/m3.90
    螺旋桨转速/(r/min)1 200
    下载: 导出CSV

    表  2  EMRAX电动机输出特性

    Table  2.   Output characteristics of EMRAX motors

    参数 型号
    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
    下载: 导出CSV

    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
    下载: 导出CSV

    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
    下载: 导出CSV

    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
    下载: 导出CSV

    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
    下载: 导出CSV

    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
    下载: 导出CSV

    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
    下载: 导出CSV
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  • 收稿日期:  2022-09-15
  • 网络出版日期:  2023-11-27

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