A component (100) for an aircraft (200) and an aircraft (200) comprising such component is provided. The component (100) comprises at least one heat source, (110) a housing (140) enclosing the at least one heat source (110), at least one heat exchanger (120), at least one heat sink (130), at least one structural suspension element (150), and an air duct (170). Each of the at least one structural suspension element (150) is attached to an inner surface of the housing (140) and supports one or more of the at least one heat source (110) within the housing (140). The heat sink (130) is part of the housing (140) and is configured to guide air from an inside of the housing (140) to an outside of the housing (140). Each of the at least one heat exchanger (120) is thermally coupled to at least one of the at least one heat source (110). Each of the at least one heat exchanger (120) is fluidly connected to one of the at least one heat sink (130) via an inlet line (160) and a return line (161) for a coolant. The air duct (170) is configured to guide ambient air from the outside through the housing (140), past each of the at least one structural suspension element (150), and through the heat sink (130) out of the housing (140).


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    Title :

    STRUCTURAL COOLING SYSTEM FOR AN AIRCRAFT


    Additional title:

    STRUKTURELLES KÜHLSYSTEM FÜR EIN FLUGZEUG
    SYSTÈME DE REFROIDISSEMENT STRUCTUREL POUR UN AÉRONEF


    Contributors:

    Publication date :

    2023-12-06


    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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