An aircraft landing gear shock absorber strut (24) comprising: an outer cylinder (26) having a bore defining an opening; an inner cylinder (28) having a first end region movably coupled within the bore and a second end region which projects out of the opening, the inner cylinder being arranged to move along a longitudinal axis of the bore between a first condition in which the shock absorber strut is compressed and a second condition in which the shock absorber strut is extended, the inner cylinder being biased by a spring force to assume the second condition; a mechanical outstop (OS) arranged to engage an abutment surface of the inner cylinder to limit extension of the shock absorber strut; and a rotatable member defining a threaded surface (TS) configured to drive the out stop axially to move the inner cylinder from the second condition towards the first condition to compress the shock absorber strut, the rotatable member being arranged such that the spring force cannot rotate the rotatable member to allow the shock absorber strut to extend.


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    Titel :

    AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT


    Weitere Titelangaben:

    STOSSDÄMPFERSTREBE EINES FLUGZEUGFAHRWERKS
    JAMBE D'AMORTISSEUR DE TRAIN D'ATTERRISSAGE D'AVION


    Beteiligte:

    Erscheinungsdatum :

    2023-01-25


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein



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