The invention relates generally to an aircraft landing gear steering system (110, 210, 310) comprising a turning member (118, 218, 318) that is operably coupled to a landing gear leg (116, 216, 316) through a harmonic drive mechanism (260, 360). The landing gear steering system (110, 210, 310) may be electrically driven. Additionally, the landing gear system (110, 210, 310) has various advantages, including the provision of a safe failure mode should the harmonic drive mechanism (260, 360) fail.
AIRCRAFT LANDING GEAR STEERING SYSTEM
SYSTEME DE DIRECTION D'ATTERRISSEUR D'AERONEF
2016-09-13
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2017
|European Patent Office | 2016
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