Patent (Patents)
Lubrication mechanism design for aircraft landing gear bearings
Heirendt, Laurent; Hugh, Hugh H.T.; Wang, Phillip
2018
 

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Abstract :
[en] 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.
Disciplines :
Aerospace & aeronautics engineering
Inventor :
Heirendt, Laurent  ;  University of Luxembourg > Luxembourg Centre for Systems Biomedicine (LCSB)
Hugh, Hugh H.T.;  University of Toronto - U of T > Institute for Aerospace Science
Wang, Phillip;  Safran Landing Systems Canada Inc.
Language :
English
Title (54) :
Lubrication mechanism design for aircraft landing gear bearings
Publication date (43-45) :
20 December 2018
Filing date (22) :
14 June 2017
Patent/publication number (10-11) :
US2018/0363723A1
Patent status (13) :
A
Priority number (30) :
15/62,863
International classification (IPC) (51) :
F16C29/02; F16C33/10; F16F7/09; F16F7/112
European classification (ECLA) (52) :
F16C29/025; F16C33/10; F16F7/09; F16F7/112; F16C2326/05; F16C2326/43
Applicant (71) :
Safran Landing Systems Canada Inc., Ajax (CA)
Publication organism (19) :
US Patent Office
Available on ORBilu :
since 17 January 2019

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