An anti-torque rotor (4, 4') of a helicopter (1), having : a supporting body (14, 14'); a drive shaft (10, 10') which rotates about a first axis (B) with respect to the supporting body (14, 14'); a hub (11) connected operatively to drive shaft (10, 10') and angularly fixed with respect to first axis (B); at least one blade (12) which is connected operatively to hub (11), is angularly fixed with respect to first axis (B), and is angularly movable with respect to a second axis (D) to adjust the pitch angle of blade (12); and an actuator (16, 16') which can be operated to rotate blade (12) about second axis (D) to adjust the pitch angle of blade (12); actuator (16, 16') has an electric motor (25, 25') which generates torque along the first axis (B); and a mechanical stage (30, 30') interposed between the electric motor (25, 25') and blade (12), and designed to convert the torque into rotation of blade (12) about the respective second axes (D); electric motor (25, 25') is fixed to supporting body (14, 14').


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    Titel :

    Helicopter anti-torque rotor


    Weitere Titelangaben:

    Drehmomentausgleichsrotor eines Hubschraubers
    Rotor anticouple d'hélicoptère


    Beteiligte:
    WANG JAMES (Autor:in)

    Erscheinungsdatum :

    10.02.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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