一种电动飞机概念方案的参数设计方法

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。 

A sizing method of all-electric aircraft for conceptual design

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.