A shock absorber with lubricated bearings for an aircraft landing gear includes a piston that is received in a cylinder, and an upper bearing fixed to the piston that slidably engages an inner surface of the cylinder. A lower bearing extends inwardly from a lower portion of the cylinder and engages an outer surface of the piston. The lower bearing has a center axis and defines an annular bearing surface configured to slidably engage the piston outer surface. The annular bearing surface has a first portion that extends circumferentially more than one hundred eighty degrees about the center axis at a constant radius, defining a circular annular segment. A second portion closes the circular annular segment and defines a shallow channel or pocket in the annular bearing surface. In some embodiments the lower bearing further comprises oppositely disposed frustoconical thrust portions.


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    Titel :

    LUBRICATION MECHANISM DESIGN FOR AIRCRAFT LANDING GEAR BEARINGS


    Weitere Titelangaben:

    SCHMIERMECHANISMUSDESIGN FÜR FLUGZEUGFAHRWERKLAGER
    CONCEPTION DE MÉCANISME DE LUBRIFICATION POUR PALIERS DE TRAIN D'ATTERRISSAGE D'AÉRONEF


    Beteiligte:
    HEIRENDT LAURENT (Autor:in) / LIU HUGH H T (Autor:in) / WANG PHILLIP (Autor:in)

    Erscheinungsdatum :

    24.02.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F16F SPRINGS , Federn / B64C AEROPLANES , Flugzeuge / F16C SHAFTS , Wellen / F16J Kolben , PISTONS



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