A cooling system for a fuel tank (24) of an aircraft includes a temperature sensor (140), a cooling system (70), and a control module (72). The temperature sensor (140) detects a fuel temperature within the fuel tank. The cooling system (70) maintains the fuel temperature below a control temperature. The phase change cooling system (92) includes a heat exchanger (86). A cooling fluid (94) flows through the heat exchanger (86) and is in thermal communication with a surface (50) of the fuel tank (24). The control module (72) is in signal communication with the temperature sensor (140) and the cooling system (70). The control module (72) includes control logic for monitoring the temperature sensor (140), determining if the fuel temperature is above the control temperature, and generating an activation signal.


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    Titel :

    FUEL TANK OF AN AIRCRAFT AND COOLING SYSTEM


    Weitere Titelangaben:

    KRAFTSTOFFTANK EINES FLUGZEUGS UND KÜHLSYSTEM
    RÉSERVOIR D'AVION ET SYSTÈME DE REFROIDISSEMENT


    Beteiligte:
    MORAVEC BRADFORD A (Autor:in) / GRAHAM RODNEY N (Autor:in) / GRIM ALAN (Autor:in) / MULVANEY PATRICK J (Autor:in) / ADKINS II DAVID A (Autor:in) / OLSON ERIC C (Autor:in) / JOJIC IVANA (Autor:in) / THORNTON MARK M (Autor:in) / BELIÉRES JEAN-PHILIPPE A (Autor:in)

    Erscheinungsdatum :

    2020-02-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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