FUEL SUPPLY SYSTEM FOR HYDROGEN AIRCRAFT, AND TANK INTERNAL PRESSURE ADJUSTMENT METHOD

A fuel supply system (1) for a hydrogen-powered aircraft includes: a fuel tank (2) that stores liquefied hydrogen; a pump (5) that discharges the liquefied hydrogen from the fuel tank (2) to supply the liquefied hydrogen to a propulsion device (102); a pressure increasing mechanism (3) that increase...

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Bibliographische Detailangaben
Hauptverfasser:	SHIMIZU, Kazuko, YASUDA, Shigenori, SASAKI, Koichi, TSURU, Kazunari, TANAKA, Shota
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A fuel supply system (1) for a hydrogen-powered aircraft includes: a fuel tank (2) that stores liquefied hydrogen; a pump (5) that discharges the liquefied hydrogen from the fuel tank (2) to supply the liquefied hydrogen to a propulsion device (102); a pressure increasing mechanism (3) that increases a tank internal pressure being a pressure in an inner part of the fuel tank (2); a flow rate controller (71) that controls a flow rate of the liquefied hydrogen to be supplied from the fuel tank (2) to the propulsion device (102); and a pressure controller (73) that controls, on the basis of information which is about the flow rate of the liquefied hydrogen and is input from the flow rate controller (71), the pressure increasing mechanism (3) to adjust the tank internal pressure.