一种电动飞机概念方案的参数设计方法

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.