分布式电推进飞机动力系统评估优化方法

Taking the electric propulsion aircraft power system as the research object, we conduct the following research. The power flow calculation method for the power system is used to analyze the distributed electric propulsion aircraft electrical system with the high-voltage DC power supply system; the energy flow relationship between the electrical system in the stable operating state and the open circuit fault state is simulated; the influence of the DC voltage level on the electrical system is analyzed. A complete distributed electric propulsion aircraft power system simulation model is built. The advantages and disadvantages of pure electric propulsion and turbo electric propulsion architectures in terms of three evaluation indicators (propulsion power, propulsion efficiency, and range) are comparatively analyzed. A parametric model of typical components of the power system is established and then optimized by the signomial geometric programming algorithm. The optimized trade-off relationship between the power system quality and fuel consumption rate with the traditional turbo propulsion and turbo-electric propulsion architectures is compared. The research results provide a valuable forward design method for the design of hybrid propulsion systems for electric propulsion aircraft.