A shrink mechanism for use with a landing gear of an aircraft is provided. The landing gear includes an outer sleeve at least partially surrounding a shock strut, the shrink mechanism has a shaft rotatably coupled to the outer sleeve about a shaft rotation axis, the shaft being disposed perpendicular to a centerline of the shock strut, an anchor arm coupled to the shaft, the anchor arm being configured to couple to a structure within a wing of the aircraft, a shrink arm coupled to the shaft, the shrink arm and the anchor arm being coupled to the shaft so as to rotate as a unit with the shaft about the shaft rotation axis, and a shrink link rotatably coupled to the shrink arm, the shrink link being configured to rotatably couple to the shock strut.


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    Titel :

    Semi-levered shrink landing gear


    Beteiligte:
    DAHL BRUCE A (Autor:in) / SAKURAI SEIYA (Autor:in)

    Erscheinungsdatum :

    13.10.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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