An encapsulated shock absorber of an aircraft undercarriage includes a sliding rod slidably mounted in a leg strut of the undercarriage and an inner cylinder extending inside the strut. The inner cylinder is fastened to the strut via a top end, and the rod slides around the inner cylinder. The inner cylinder is terminated inside the sliding rod by a diaphragm that defines an oil chamber in the shock absorber and inside the sliding rod. A mixed oil/gas chamber is located in the inner cylinder, and an expansion chamber extends between the sliding rod and the inner cylinder. A hole being made in the inner cylinder in register with the expansion chamber is connected by a pipe to a pressure sensor situated outside the strut. The pipe extends inside the inner cylinder from the hole to the top end of the inner cylinder.


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    Titel :

    MEASURING THE PRESSURE IN THE EXPANSION CHAMBER OF AN ENCAPSULATED SHOCK ABSORBER IN AN AIRCRAFT LANDING GEAR


    Beteiligte:
    HENRION PHILIPPE (Autor:in) / LAFITTE ARNAUD (Autor:in)

    Erscheinungsdatum :

    2023-02-09


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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