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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    Title :

    AIRCRAFT LANDING GEAR STEERING SYSTEM


    Additional title:

    SYSTEME DE DIRECTION D'ATTERRISSEUR D'AERONEF


    Contributors:

    Publication date :

    2016-09-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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