分布式电推进飞机动力系统评估优化方法

以电推进飞机的动力系统作为研究对象，开展了以下研究工作：采用电力系统潮流计算方法，分析了采用高压直流供电体制的分布式电推进飞机电气系统，模拟了其在稳定运行状态与断路故障状态下的能量流动关系，同时分析了直流电压等级对电气系统的影响。搭建了完整的分布式电推进飞机动力系统仿真模型，依据基于时间和基于高度的飞行剖面，对比分析了纯电推进与涡轮电推进架构在推进功率、推进效率与航程3个评价指标上的优劣。建立了动力系统典型部件的参数化模型，并使用符号规划算法对建立的参数化模型进行了优化计算，比较了传统涡轮推进与涡轮电推进架构下动力系统质量与燃油消耗率间的优化权衡关系。研究结果为分布式电推进飞机混合动力系统的设计提供了有价值的正向设计方法。

Evaluation and optimization method for power systems of distributed electric propulsion aircraft

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.