An aircraft fuel tank inerting system (10) may include at least one fuel tank (14, 16, 18), at least one surge tank (20, 22), an inert air assembly (12), at least one fluid valve (24, 26, 28) connected to the at least one fuel tank (14, 16, 18), the at least one surge tank (20, 22), and the inert air assembly (12), and/or an electronic control unit (30). The electronic control unit (30) may be configured to control the at least one fluid valve (24, 26, 28) to provide inert air (34) from the inert air assembly (12) to the at least one fuel tank (14, 16, 18) and/or to the at least one surge tank (20, 22). The electronic control unit (30) may be configured to control the at least one fluid valve (24, 26, 28) to provide the inert air (34) from the inert air assembly (12) to the fuel tank during a climb phase of a flight and control the at least one fluid valve (24, 26, 28) to provide inert air (34) from the inert air assembly (12) to the at least one surge tank (20, 22) during a descent phase of the flight.


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    Titel :

    AIRCRAFT FUEL TANK INERTING SYSTEM


    Weitere Titelangaben:

    INERTISIERUNGSSYSTEM FÜR EINEN FLUGZEUGTREIBSTOFFTANK
    SYSTÈME D'INERTAGE POUR RÉSERVOIR DE CARBURANT D'AÉRONEF


    Beteiligte:

    Erscheinungsdatum :

    2022-06-08


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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