氢燃料飞机在推进系统、燃料储运系统及机体结构等方面相比于传统飞机发生较大改变。首先，本文建立燃料电池混合动力系统模型，将燃料电池的极化损失与风扇发动机总体性能相集成；然后，建立了液氢储罐及供氢模型、评估了液氢供给过程中罐内压力和温度的变化规律；其次，进行了飞机三维几何建模和快速气动评估，分析了集成液氢储罐对全机气动特性的影响，得到了全机升阻特性随机身外形的变化规律。综合考虑燃料储存能量、推进系统功率及储罐结构设计，随飞机携带能量增加，液氢储罐重量效率最高可达80%。本文将燃料电池混合动力系统的耗油率与质量均考虑在内，优化氢燃料储罐布置，实现了液氢飞机的燃料储运、推进系统、飞机机身结构的多维度匹配，得到液氢飞机的飞发匹配方案。研究还表明，仅增加机身长度，飞机的升阻比变化较小；氢能飞机减少的碳排放量、氢罐的重量效率均与机身长度的加长量呈正相关；当机身长度加长5%时，碳排放量可减少714kg，减碳程度为1.56%；当机身长度加长20%时，碳排放量可减少45709kg，减碳程度为100%，巡航时间超过传统飞机7.08%。
Compared with traditional aircraft, hydrogen fuel cell aircraft undergo significant changes in aspects such as propul-sion systems, fuel storage and transportation systems, and airframe structure. First, this paper establishes a fuel cell hybrid power system model, integrating the polarization losses of the fuel cell with the overall performance of the fan engine. Then, liquid hydrogen storage tank and hydrogen supply models are developed, and the pressure and tem-perature variations inside the tank during the hydrogen supply process are evaluated. Next, three-dimensional geo-metric modeling of the aircraft is performed, along with rapid aerodynamic assessment, analyzing the impact of inte-grating the liquid hydrogen tank on the overall aerodynamic characteristics of the aircraft. The variation of the aircraft's lift-to-drag ratio with the external shape is obtained. By considering fuel storage energy, propulsion system power, and tank structural design, as the aircraft carries more energy, the weight efficiency of the liquid hydrogen storage tank can reach up to 80%. This paper considers both the fuel consumption rate and mass of the fuel cell hybrid power system, optimizes the layout of the hydrogen fuel tank, and achieves a multi-dimensional match of fuel storage and transporta-tion, propulsion system, and aircraft body structure for the liquid hydrogen aircraft. The study also shows that simply increasing the fuselage length results in a small change in the lift-to-drag ratio. The reduction in carbon emissions and the weight efficiency of the hydrogen tank are positively correlated with the increase in fuselage length. When the fu-selage length is extended by 5%, the carbon emission can be reduced by 714 kg, achieving a 1.56% reduction in car-bon emissions. When the fuselage length is extended by 20%, the carbon emission can be reduced by 45,709 kg, achieving a 100% reduction in carbon emissions, and the cruising time exceeds that of traditional aircraft by 7.08%.
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