| 摘要 |
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.
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