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.


    Access

    Download


    Export, share and cite



    Title :

    Semi-levered shrink landing gear


    Contributors:

    Publication date :

    2020-10-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    SEMI-LEVERED SHRINK LANDING GEAR

    DAHL BRUCE A / SAKURAI SEIYA | European Patent Office | 2023

    Free access

    Semi-levered shrink landing gear

    DAHL BRUCE A / SAKURAI SEIYA | European Patent Office | 2023

    Free access

    Semi-levered shrink landing gear

    DAHL BRUCE A / SAKURAI SEIYA | European Patent Office | 2023

    Free access

    SEMI-LEVERED SHRINK LANDING GEAR

    DAHL BRUCE A / SAKURAI SEIYA | European Patent Office | 2020

    Free access

    SEMI-LEVERED SHRINK LANDING GEAR

    BRUCE A DAHL / SAKURAI SEIYA | European Patent Office | 2018

    Free access