An aircraft includes a landing gear having a shock strut, an outer sleeve at least partially surrounding the shock strut, and a shrink mechanism coupled to both the outer sleeve and the shock strut, where the shrink mechanism moves the shock strut relative to the outer sleeve. The shrink mechanism includes a shaft rotatably coupled to the outer sleeve, an anchor arm coupled to the shaft, 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 a shaft rotation axis, relative to the outer sleeve, at least 180° when the anchor arm is coupled to the structure within the wing of the aircraft, and a shrink link rotatably coupled to the shrink arm, the shrink link being configured to rotatably couple to the shock strut.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    SEMI-LEVERED SHRINK LANDING GEAR


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

    Erscheinungsdatum :

    2020-12-24


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    SEMI-LEVERED SHRINK LANDING GEAR

    DAHL BRUCE A / SAKURAI SEIYA | Europäisches Patentamt | 2023

    Freier Zugriff

    Semi-levered shrink landing gear

    DAHL BRUCE A / SAKURAI SEIYA | Europäisches Patentamt | 2020

    Freier Zugriff

    SEMI-LEVERED SHRINK LANDING GEAR

    DAHL BRUCE A / SAKURAI SEIYA | Europäisches Patentamt | 2023

    Freier Zugriff

    Semi-levered shrink landing gear

    DAHL BRUCE A / SAKURAI SEIYA | Europäisches Patentamt | 2023

    Freier Zugriff

    Semi-levered shrink landing gear

    DAHL BRUCE A / SAKURAI SEIYA | Europäisches Patentamt | 2023

    Freier Zugriff