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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    Title :

    FUEL TANK OF AN AIRCRAFT AND COOLING SYSTEM


    Additional title:

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



    Publication date :

    2020-02-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    Aircraft fuel tank system

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    Aircraft fuel tank system

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    LYNAS CHRISTOPHER / JAMES PETER WILLIAM | European Patent Office | 2016

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    Aircraft fuel tank system

    LYNAS CHRISTOPHER / JAMES PETER WILLIAM / MACGREGOR KEITH | European Patent Office | 2016

    Free access

    Aircraft fuel tank system

    LYNAS CHRISTOPHER / JAMES PETER WILLIAM / MACGREGOR KEITH | European Patent Office | 2016

    Free access