HYDROGEN OPTIMIZED AIRCRAFT ARCHITECTURE AND OPERATIONS

Abstract: a dual fuel propulsion system is disclosed. the aircraft is capable of performing a flight mission during which the first or the second selectively useable. the aircraft comprises: at least one internal combustion engine capable of generating propulsive thrust using selectively a first kerosene based jet fuel and a second liquid hydrogen fuel, and two independent sets of fuel systems, including a first fuel system feeding the first fuel from a first set of fuel storage tanks to the internal combustion engine and a second fuel system feeding the second fuel from a second set of fuel storage tanks to the internal combustion engine. both sets of fuel storage tanks host the required fuel for the flight mission plus reserve fuel.

Inventor(s): Martin NÜSSELER

CPC Classification: B64D37/30 (EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT)

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