一种电动飞机概念方案的参数设计方法
doi: 10.13224/j.cnki.jasp.20220084
A sizing method of all-electric aircraft for conceptual design
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摘要:
为了准确地进行电动飞机概念方案的设计评估，从其自身特征出发，结合任务需求和不同飞行阶段的能耗分析，建立了全机总质量评估模块；为了完成方程的封闭和满足必要的飞行性能约束，建立了参数矩阵图模块；搭建的设计系统可以有效评估起飞总质量、翼载荷、功率载荷和翼展等总体参数。基于该系统，对国内外三款电动飞机进行设计和对比分析：不同机型下，程序所得的各项质量、翼面积、展长和翼载荷等均与实际数据相近；各项数据对比的绝对数值差异反映出对于任务的模拟和能耗在合理范围之内，且其相对误差对于初级设计阶段的总体参数评估而言，也是可以接受的。这些研究结果不仅验证了本文设计方法的正确性和可行性，还表明了该方法可为电动飞机初步的参数选定和性能评估提供重要的设计支撑。
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关键词:
- 电动飞机 /
- 电推进系统 /
- 飞机设计 /
- 质量评估 /
- 参数矩阵图
Abstract:In order to evaluate the sizing of all-electric aircraft for conceptual design precisely, a total mass evaluation module was established, which was combined with its own design features, mission requirements and energy consumption analysis. A sizing matrix plot module was established to enclose the equations and fulfill some performance constraints. The design system can assess take-off mass, wing loading, power loading and some crucial sizing parameters, like wing area and wingspan. Based on this system, three domestic and international all-electric aircrafts were adopted for design and comparison: for different aircraft types, the mass, wing area, wingspan, wing load and other design parameters obtained by the program were all close to the actual data; the absolute numerical difference of the data comparison indicated that the simulation and energy consumption of the mission were within a reasonable range. And the relative numerical differences were also acceptable for the overall parameter evaluation in the conceptual design stage. The results show that it can verify the validity and feasibility of the developed method, and can also support the all-electric aircraft design with parameter selection and performance evaluation.
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Key words:
- all-electric aircraft /
- electric propulsion system /
- aircraft design /
- mass evaluation /
- sizing matrix plot
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图 1 参数矩阵图方法示意图
Figure 1. Sschematic plot of sizing matrix plot method
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图 2 设计系统工作流程示意图
Figure 2. Work-flow of design system
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图 3 针对E430的参数矩阵图
Figure 3. Sizing matrix plot for E430
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图 4 本文设计方法对于E430输出的部分结果
Figure 4. Partial output results of the paper design method for E430
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图 5 参数更新后的参数矩阵图和起飞总质量
Figure 5. Updated sizing matrix plot and maximum takeoff mass
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图 6 针对eFlyer 2的参数矩阵图
Figure 6. Sizing matrix plot for eFlyer 2
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图 7 程序对于eFlyer 2输出的部分结果
Figure 7. Partial output results of the program for eFlyer 2
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图 8 针对Taurus Electro G2.5的参数矩阵图
Figure 8. Sizing matrix plot for Taurus Electro G2.5
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图 9 程序对于 Taurus Electro G2.5输出的部分结果
Figure 9. Partial output results of the program for Taurus Electro G2.5
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表 1 E430的输入参数
Table 1. Input data of E430
参数 数值 飞机 机组和有效载荷总质量/kg 180 展弦比 16.7 Oswald效率因子 0.82* 电推进系统 螺旋桨数量 1 螺旋桨效率 0.8* 换流器（逆变器）效率 0.98* 控制器效率 0.95 电动机效率 0.9 电动机功率密度/（W/kg） 2100 电池功率密度/（W/kg） 801 电池能量密度/（Wh/kg） 153.7 任务需求与
性能参数航程/km 170 最大巡航速度/（km/h） 150 巡航高度/m 1000 巡航速度/（km/h） 90 失速速度/（km/h） 60 爬升率/（m/s） 3.5 盘旋高度/m 460* 盘旋时间/min 1* 起飞滑跑距离/m 260 着陆滑跑距离/m 180 绝对升限/m 3500* 实用升限/m 3000*
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表 2 E430实际构型和程序输出的总体参数对比
Table 2. Comparison of real and simulated data of overall parameters for E430
参数 实际数据 程序输出 相对误差/% Mto/kg 470 504.9 7.43 Ma/kg 199 220.2 10.65 Mb/kg 72 86.6 20.28 Mm/kg 19 18.1 −4.74 机翼面积/m2 11.37 13.67 20.23 机翼展长/m 13.80 15.11 9.49 翼载荷/（kg/m2） 41.34 36.93 −10.65
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表 3 更新后实际构型和程序输出的总体参数对比
Table 3. Comparison of updated real and simulated data of overall parameters
参数 实际数据 程序输出 相对误差/% Mto/kg 470 484.9 3.17 Ma/kg 199 199 0 Mb/kg 72 86.3 19.86 Mm/kg 19 19.6 3.16 机翼面积/m2 11.37 11.67 2.64 机翼展长/m 13.80 13.96 1.16 翼载荷/（kg/m2） 41.34 41.55 0.52
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表 4 eFlyer 2的输入参数
Table 4. Input data of eFlyer 2
参数 数值 飞机 机组和有效载荷总质量/kg 200 展弦比 12 Oswald效率因子 0.8* 电推进系统 螺旋桨数量 1 螺旋桨效率 0.8* 换流器（逆变器）效率 0.98* 控制器效率 0.95* 电动机效率 0.93 电动机功率密度/（W/kg） 2500 电池功率密度/（W/kg） 1300 电池能量密度/（Wh/kg） 250 任务需求与
性能参数航程/km 330 最大巡航速度/（km/h） 250 巡航高度/m 3048 巡航速度/（km/h） 178 失速速度/（km/h） 89 爬升率/（m/s） 6.1 盘旋高度/m 460* 盘旋时间/min 5* 起飞距离/m 350 着陆距离/m 350 绝对升限/m 4260 实用升限/m 4000
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表 5 eFlyer 2实际构型和程序输出的总体参数对比
Table 5. Comparison of real and simulated data for eFlyer 2
参数 实际数据 程序输出 相对误差/% Mto/kg 862 915.6 6.22 Ma/kg 365 385.8 5.70 Mb/kg 253 281.6 11.30 Mm/kg 44 48.2 9.55 机翼面积/m2 12 11.83 −1.42 机翼展长/m 12 11.91 −0.75 翼载荷/（kg/m2） 71.83 77.40 7.74
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表 6 Taurus Electro G2.5的输入参数
Table 6. Input data of Taurus Electro G2.5
参数 数值 飞机 机组和有效载荷总质量/kg 200 展弦比 18.3 Oswald效率因子 0.82* 电推进系统 螺旋桨数量 1 螺旋桨效率 0.8* 换流器（逆变器）效率 0.98* 控制器效率 0.95* 电动机效率 0.9 电动机功率密度/（W/kg） 2800 电池功率密度/（W/kg） 1000 电池能量密度/（Wh/kg） 200 任务需求与
性能参数航程/km 90 最大巡航速度/（km/h） 150 巡航高度/m 1000 巡航速度/（km/h） 110 失速速度/（km/h） 63 爬升率/（m/s） 3.1 盘旋高度/m 460* 盘旋时间/min 1* 起飞距离/m 245 着陆距离/m 270 绝对升限/m 4200 实用升限/m 3900
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表 7 Electro G2.5实际构型和程序输出的总体参数对比
Table 7. Comparison of real and simulated data of overall parameters for Electro G2.5
参数 实际数据 程序输出 相对误差/% Mto/kg 550 580.2 5.49 Ma/kg 297 318.8 7.34 Mb/kg 42 48.8 16.19 Mm/kg 11 12.6 14.55 机翼面积/m2 12.26 11.61 −5.30 机翼展长/m 14.97 14.58 −2.61 翼载荷/（kg/m2） 44.86 49.97 11.40
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Aircraft information taurus electro G2.5 2019[EB/OL]. [2021-10-23]. https://www.pipistrel-usa.com/wp-content/uploads/Pipistrel-Taurus-Electro-Information-Pack-R2.pdf -
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