氢燃料飞机在推进系统、燃料储运系统和机体结构等方面相比于传统飞机发生较大改变。首先，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电驱动风扇发动机总体性能相集成；其次，建立了液氢储罐和供氢模型，评估了液氢供给过程中罐内压力和温度的变化规律；然后，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。综合考虑了燃料储存能量、推进系统功率和储罐结构设计，随着飞机携带能量增加，液氢储罐质量效率最高可达80%。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系统、推进系统、飞机机体结构的多维度匹配，得到液氢飞机的飞发匹配方案。研究表明，仅增加机身长度时，飞机的升阻比变化较小；氢能飞机减少的碳排放量、氢罐的质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714 kg，减碳比例为1.56%；当机身长度加长20%时，碳排放量可减少45 709 kg，减碳比例为100%，巡航时间超过传统飞机的10.04%。

Compared with traditional aircraft， hydrogen-powered aircraft undergo significant changes in aspects such as propulsion systems， fuel storage and transportation systems， and airframe structure. Firstly， a fuel cell hybrid power system model is established， integrating the polarization losses of the fuel cell with the overall performance of the electric-driven fan engine. Then， liquid hydrogen storage tank and hydrogen supply models are developed， and the pressure and temperature variations inside the tank during the hydrogen supply process are evaluated. Next， three-dimensional geometric modeling of the aircraft is performed， along with rapid aerodynamic assessment， and the impact of integrating the liquid hydrogen tank on the overall aerodynamic characteristics of the aircraft is analyzed. 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%. Considering both the fuel consumption rate and mass of the fuel cell hybrid power system， the layout of the hydrogen fuel tank is optimized， and a multi-dimensional match of fuel storage and transportation systems， propulsion systems， and aircraft airframe structure for the liquid hydrogen-powered aircraft is achieved，resulting in an integrated airframe-propulsion matching scheme. The study further 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 fuselage length is extended by 5%， the carbon emission can be reduced by 714 kg， corresponding to a 1.56% reduction rate. When the fuselage length is extended by 20%， the carbon emission can be reduced by 45 709 kg， achieving a 100% reduction rate， and the cruising time exceeds that of traditional aircraft by 10.04%.