An aircraft landing gear shock absorber strut 50 comprises: an outer cylinder 52 and a sliding tube 54 within the outer cylinder 52 so as to be movable between compressed and extended positions, further comprising a first piston head 56 upon which pressurised oleo-pneumatic shock absorber fluid acts to force the sliding tube 54 towards the extended position; a second piston head 60 slidably mounted within the sliding tube bore; a piston restraining arrangement 62 configured to limit axial separation between the second piston 60 and the outer cylinder; and a first abutment 68 within the sliding tube bore on the opposite side of the second piston head with respect to the oleo chamber, the first abutment 68 being spaced from the second piston head when the sliding tube 54 is in the extended position, the first abutment 68 being arranged to engage the second piston 60 as the sliding tube moves from the extended position to the compressed position.


    Access

    Download


    Export, share and cite



    Title :

    Aircraft landing gear shock absorber strut


    Contributors:
    IAN BENNETT (author)

    Publication date :

    2025-01-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



    AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT

    BENNETT IAN | European Patent Office | 2025

    Free access

    AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT

    BENNETT IAN | European Patent Office | 2024

    Free access

    Aircraft landing gear shock absorber strut

    IAN ROBERT BENNETT | European Patent Office | 2025

    Free access

    AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT

    BENNETT IAN ROBERT | European Patent Office | 2024

    Free access

    AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT

    SCHMIDT ROBERT KYLE | European Patent Office | 2023

    Free access