A landing gear for use on an aircraft, the landing gear including a shock strut and an anti-rotation linkage. The shock strut is positioned at least partially within and guided in movement by a guide member coupled to a frame of the aircraft. The shock strut including an outer cylinder that is shaped and sized to engage the guide member where the guide member guides sliding movement of the outer cylinder, and where the outer cylinder is configured so as to be driven in the sliding movement relative to the guide member, and an inner cylinder disposed at least partly within the outer cylinder. The anti-rotation linkage including a connector plate coupled to the outer cylinder of the shock strut, and an anti-rotation link assembly coupled to both the guide member and the connector plate, the anti-rotation link assembly being configured to maintain the shock strut in a fixed rotational orientation relative to the guide member.


    Access

    Download


    Export, share and cite



    Title :

    Semi-levered shrink landing gear


    Contributors:

    Publication date :

    2023-11-28


    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 | 2020

    Free access

    SEMI-LEVERED SHRINK LANDING GEAR

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

    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