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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    Titel :

    AIRCRAFT LANDING GEAR STEERING SYSTEM


    Weitere Titelangaben:

    SYSTEME DE DIRECTION D'ATTERRISSEUR D'AERONEF


    Beteiligte:

    Erscheinungsdatum :

    13.09.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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