A landing gear assembly is provided. The landing gear assembly includes a shock strut. The shock strut includes a shock strut cylinder and a shock strut piston slidably disposed within the shock strut cylinder. The landing gear assembly further includes a temperature control unit assembly disposed within the shock strut cylinder. The temperature control unit assembly is configured to, responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, heat gas within the shock strut cylinder.


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    Titel :

    AIRCRAFT LANDING GEAR ENERGY ABSORPTION


    Beteiligte:
    BODKI BASAVARAJ (Autor:in) / M N HEMANTH (Autor:in)

    Erscheinungsdatum :

    17.10.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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