Semi-Physical Method for the Mass Estimation of Fuselages carrying Liquid Hydrogen Fuel Tanks in Conceptual Aircraft Design

Hydrogen-powered aircraft can contribute to the effort of reducing aviation´s climate impact. A better under-standing of the liquid hydrogen storage with respect to airframe integration is required to improve the predictive qualities of overall aircraft design studies. This paper presents the synthesis of loads and mass estimation models in hydrogen aircraft design. A case study is performed on the assessment of non-integral liquid hydro-gen tanks and their impact on the fuselage structure. The introduction of loads analysis and analytical design of primary fuselage structures is able to capture more design sensitivities compared to a design process that fully relies on empirical methods. Technical challenges of the fuel tank integration in the rear of the fuselage are reviewed and critical design parameters discussed.