Systems and methods are provided for storage in at least one on-board fuel tank of aircraft fuel under a predetermined pressure and at an internal ambient tank temperature. A passive heat exchanger having an exchanger inlet is fluid-connected to a propulsion engine of the aircraft to receive heated pressurized bleed air therefrom while an exchanger outlet is fluid connected to the fuel tank. The passive heat exchanger is configured to cool the heated pressurized bleed air from the engine by heat transfer to a surrounding environment by radiation and convection so as to supply pressurization air to the fuel tank at the predetermined internal tank pressure and the internal ambient tank temperature. A system controller is provided to provide the fuel tank with pressurized air at a predetermined temperature during various aircraft flight phases.


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    Title :

    AIRCRAFT FUEL TANK PRESSURIZATION SYSTEMS AND METHODS



    Publication date :

    2021-03-25


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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