Reference : Lubrication mechanism design for aircraft landing gear bearings |
Patent : Patent | |||
Engineering, computing & technology : Aerospace & aeronautics engineering | |||
http://hdl.handle.net/10993/38357 | |||
Lubrication mechanism design for aircraft landing gear bearings | |
English | |
Heirendt, Laurent ![]() | |
Hugh, Hugh H.T. [University of Toronto - U of T > Institute for Aerospace Science] | |
Wang, Phillip [Safran Landing Systems Canada Inc.] | |
20-Dec-2018 | |
2017-06-14 | |
US Patent Office | |
US2018/0363723A1 | |
15/62,863 | |
A | |
United States | |
Safran Landing Systems Canada Inc., Ajax (CA) | |
F16C29/02; F16C33/10; F16F7/09; F16F7/112 | |
F16C29/025; F16C33/10; F16F7/09; F16F7/112; F16C2326/05; F16C2326/43 | |
US, CA, CN | |
AL, AT, BE, BG, CH, CY, CZ, DE, DK, EE, ES, FI, FR, GB, GR, HR, HU, IE, IS, IT, LI, LT, LU, LV, MC, MK, MT, NL, NO, PL, PT, RO, RS, SE, SI, SK, SM, TR | |
[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. | |
Researchers ; Professionals ; General public | |
http://hdl.handle.net/10993/38357 | |
https://patents.google.com/patent/US20180363723A1/en |
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