一种分布式电推进飞机的多学科参数快速估计方法

A Fast Multidisciplinary Parameter Estimation Method for Distributed Electric Propulsion Aircraft

由于分布式电推进飞机综合性能显著,各个学科的交叉性强,是未来航空领域飞行器发展的趋势,因此建立一种适用于总体设计阶段的多学科参数评估方法对分布式电推进飞机的设计有着重大的意义。为了提高电动飞机在初始设计阶段的效率,本文提出了一种分布式电推进飞机的多学科参数快速估计方法。该方法对分布式电推进飞机进行总体建模并搭建能源系统框架,使用基于势流理论的简化气动分析方法对螺旋桨与机翼的气动—推进耦合特性进行分析。经仿真验证,该简化气动模型可以较好地模拟螺旋桨与机翼的气动—推进耦合特性。利用该方法在设定的飞行剖面下对某分布式电推进飞机进行多学科参数快速估计,得到了整个飞行剖面下的飞机气动性能变化及电推进系统的性能变化,为分布式电推进飞机的总体设计提供了支撑。

Due to the significant overall performance and strong interdisciplinary nature of distributed electric propulsion aircraft,it is a trend in the future development of aircraft in the aviation industry.Therefore,establishing a multidisciplinary parameter evaluation method applicable to the conceptual design phase of distributed electric propulsion aircraft is of great fundamental significance for their design.To improve the efficiency of electric aircraft in the initial design phase,this paper proposes a rapid multidisciplinary parameter estimation method for distributed electric propulsion aircraft.This method involves the overall modeling of distributed electric propulsion aircraft and the establishment of an electric power system framework.It utilizes a simplified aerodynamic analysis method based on potential flow theory to analyze the aerodynamic-propulsive coupling characteristics between the propellers and the wings.Through simulation validation,it is demonstrated that the simplified aerodynamic model can effectively simulate the aerodynamic-propulsive coupling characteristics between the propellers and the wings.Using this method,a rapid multidisciplinary parameter estimation is performed on a specific distributed electric propulsion aircraft under a set flight profile,obtaining the variations in the aircraft’s aerodynamic performance and the performance of the electric propulsion system throughout the flight profile,providing support for the conceptual design of distributed electric propulsion aircraft.