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.
LUBRICATION MECHANISM DESIGN FOR AIRCRAFT LANDING GEAR BEARINGS
SCHMIERMECHANISMUSDESIGN FÜR FLUGZEUGFAHRWERKLAGER
CONCEPTION DE MÉCANISME DE LUBRIFICATION POUR PALIERS DE TRAIN D'ATTERRISSAGE D'AÉRONEF
24.02.2021
Patent
Elektronische Ressource
Englisch
LUBRICATION MECHANISM DESIGN FOR AIRCRAFT LANDING GEAR BEARINGS
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