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


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    Titel :

    Cooling System for a Center Wing Tank of an Aircraft


    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) / BELIÈRES JEAN-PHILIPPE A (Autor:in)

    Erscheinungsdatum :

    02.06.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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