An aircraft landing gear shock absorber strut 50 comprises an outer cylinder 52 defining an oleo chamber O for containing pressurised oleo-pneumatic shock absorber fluid. It further comprises a sliding tube 52 including a piston head 56 movably mounted within the outer cylinder it being movable between a compressed position and an extended position. An annulus portion 60 is defined between the outer cylinder and the sliding tube. An out-stop member 68 is located within the annulus portion such that the piston head contacts the out-stop as the sliding tube moves from the compressed to the extended condition to limit extension of the shock absorber strut. The out-stop member comprises a resilient portion configured to be resiliently compressed in the axial direction of the outer cylinder by at least 2mm by the oleopneumatic force provided by the oleo-pneumatic shock absorber fluid. The resilient portion may be of annular shape and can comprise one or more springs. The out-stop can comprise a collar in parallel with the resilient portion, the collar having flanges which extend to overlap the resilient portion to retain it in a partially compressed state.


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    Title :

    AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT


    Additional title:

    STOSSDÄMPFERSTREBE FÜR FLUGZEUGFAHRWERK
    JAMBE D'AMORTISSEUR DE TRAIN D'ATTERRISSAGE D'AÉRONEF


    Contributors:
    BENNETT IAN (author)

    Publication date :

    2025-06-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F16F SPRINGS , Federn



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