The analysis of dynamic loads as a result of fuel sloshing should be addressed numerically and experimentally, as well as the pressure development in the tank due to the interaction of the sloshing hydrogen and the thermodynamic environment in the tank. The design solution should address the changing pressure by either active or passive means (e.g. active pressurisation control or passive anti-sloshing devices), to ensure safe operation of the engine feed systems.

The system shall manage both normal and failed system states safely. Wireless and low energy systems shall be investigated to maximise safety and maintainability. The tank should have means to safely manage overpressure cases by a venting system to minimise risk of ignition and the impacts of cryogenic temperatures. The hydrogen fuel tank should be able to facilitate applications of hydrogen burn engines as well as hydrogen fuel cell-based powertrains with minor adaptations only, permitting for either centralised boil off or distributed boil off management.

Considerations to the refuelling interface should be given, but the interface it-self is out of scope of this topic. Boundary conditions for this refuelling consideration include:

• Aircraft refuelling at a rate of approximately 5 tonnes/hour with means to refuel a cold or a warm vessel
• The cryogenic fuel will be distributed from one, or multiple tanks in the aircraft to an end user system.
• A standard coupling as an interface to refill aligned or adapted as well with other mobility sectors that allows a safe, reliable operation by the ground staff.