A thermal management system for managing the temperature of an aircraft wing comprises a gas flow path comprising a first flow path portion 224a and a second flow path portion 224b, the first flow path portion directs a flow of gas at least proximal to an aircraft component 22 for managing the component temperature, the second flow path portion receives the flow of gas from the first flow path portion and directs the flow of gas to the wing for managing the temperature of the wing for ice protection. Also provided is a method. The second flow path may extend through the leading edge of the wing. The system may comprise a temperature sensor 242 for sensing the temperature of the wing, a flow control system selectively controlling the mass flow along the second flow path portion as a function of the sensed temperature. The component may be an electric motor, a generator, power electronics.


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    Titel :

    ELECTRIC AIRCRAFT PROPULSION SYSTEM


    Weitere Titelangaben:

    ANTRIEBSSYSTEM FÜR EIN ELEKTRISCHES FLUGZEUG
    SYSTÈMES, AGENCEMENTS, STRUCTURES ET PROCÉDÉS ASSOCIÉS À UN AÉRONEF


    Beteiligte:
    WOOD NORMAN (Autor:in) / IQBAL KAMRAN (Autor:in)

    Erscheinungsdatum :

    28.09.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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