Integrating Cryogenic Tanks Model in Hydrogen Aircraft Design for Parametric Performance Analysis
Résumé
In response to the climate crisis, the aviation industry pledged through ICAO to become climate neutral by 2050. A promising solution to achieve this goal is the introduction of hydrogen-fueled aircraft, as they could emit no greenhouse gases in flight. Using hydrogen as fuel on an aircraft presents however huge challenges, especially due to its complex storage, as it must be stored in pressurized cryogenic tank. This study focuses on the integration of a medium-fidelity cryogenic hydrogen tank model into an overall aircraft design tool (FAST-OAD) and its exploitation to conduct several parametric studies on a medium-range, tube- and wing hydrogen aircraft. Results show a wide range of tank and aircraft performance, justifying the need for a hydrogen tank model in conceptual design. A strong dependency of aircraft performance on fuselage radius is highlighted, although not due to the hydrogen tank. The maximum design pressure of the tank is the second most important parameter for aircraft performance, suggesting tanks with a low design pressure differential.The increased amount of hydrogen that would need to be vented can be favorably offset by using thicker insulation, with a zero-venting design remaining feasible. A trade-off analysis between integral and non-integral tanks was also made, and it shows a small advantage to the integral configuration. With the best-identified configuration, the energy consumption of hydrogen aircraft appears to be a few percent above that of conventional aircraft at iso-technology level.
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