Improved model for hydrogen fuel cell system design and its integration in sizing for hybrid-electric-propulsion aircraft

In the present era, there exists a rising global market demand for electric propulsion aircrafts, spurred by the imperative to attain carbon peak and carbon neutrality objectives. Hydrogen fuel cell electric-propulsion aircrafts, notable for the high energy density of hydrogen and nearly zero carbon dioxide emissions, attract much attention. One crucial research orientation for these aircrafts is to develop the models of (liquid) hydrogen fuel cell system, and consider the coupling effect between the hydrogen power system design and the whole aircraft sizing. However, the current models lack detailed design modeling, analysis of the operational logic of the power generation system, as well as the correlation and impact analysis with the overall preliminary design of the whole aircraft. To address these issues, an improved model is proposed, capable of incorporating these missing factors for a more reasonable and detailed hydrogen fuel cell system design at an aircraft-level. Subsequently, the model is incorporated into the sizing procedure of electric propulsion aircrafts to facilitate the sizing of hydrogen-powered hybrid-electric-propulsion (HEP) aircrafts. The validation results and related discussions highlight that this paper refines the structural characteristics and thermodynamic properties of the cryogenic liquid hydrogen tank in a liquid hydrogen hybrid-electric aircraft. It analyzes the fundamental working logic and the dynamic operating process of the hydrogen fuel cell system, aiming to improve the rationality and accuracy of modeling for the liquid hydrogen tank. Moreover, it explains the coupling effect between the hydrogen power system design and the whole aircraft sizing, and then it compares and analyzes the performance, design characteristics and key indicators of hydrogen-powered HEP aircraft designs based on the pre-improvement model and improved model, providing a more precise focus on the mass characteristics assessment and conceptual sizing design of hydrogen-electric aircraft. Furthermore, this work can provide guidance for the design and application of other alternative energy sources.