A coaxial helicopter electronically-controlled variable pitch structure belongs to aviation machinery; an engine drives an upper rotor wing shaft to work, the upper rotor wing shaft of a helicopter is provided with an upper rotor wing propeller disk, and upper rotor wing paddles are mounted on an upper rotor wing varying pitch turntable. A small servo motor is arranged in the upper rotor wing propeller disk of the helicopter, and the small servo motor drives a worm to rotate, a turbine rotates along with the worm, the turbine is arranged on the upper rotor wing propeller disk, and is in shaft connection with the upper rotor wing varying pitch turntable, power is transferred to a lower rotor wing shaft by a set of cone gears, the work principle of the lower rotor wing shaft is same as that of the upper rotor wing shaft, the helicopter variable pitch function is achieved; the requirements to simplify the design of the structure can be met, the variable pitch control accuracy can be achieved, and rotorcraft flight characteristics can be improved.


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    Titel :

    Coaxial helicopter electronically-controlled variable pitch structure design


    Beteiligte:
    FENG JIANG (Autor:in) / ZHANG JIAXIN (Autor:in) / WANG QI (Autor:in) / DONG YUNLING (Autor:in) / JIA PENGYU (Autor:in) / YU LIBAO (Autor:in)

    Erscheinungsdatum :

    2015-12-09


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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