Relating to the field of aircraft design, the invention provides an aircraft aerodynamic configuration device. The aircraft aerodynamic configuration device includes: an outer ducted structure, an inner dynamic structure and a control surface. The outer ducted structure comprises a duct and a control steering engine for controlling the movement of the control surface, and the control steering engine is arranged on the outer wall of the duct. The inner dynamic structure includes an electric cylinder for accommodating an air-modeling ESC, a flight control system and a sensor, a propeller for providing active force, and a motor for driving the propeller to rotate. The electric cylinder, the propeller and the motor are connected in order from top to bottom in the duct height direction. The control surface for adjusting the aircraft direction is in connection with the control steering engine through a connecting rod, the inner dynamic structure and the inner wall of the outer ducted structure are fixed through a connection structure, and the control surface is located at the bottom of the duct. The aircraft aerodynamic configuration device provided by the invention solves the problem that the heavy weight of existing aircrafts seriously affects the duration of flight.


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    Titel :

    Aircraft aerodynamic configuration device


    Beteiligte:
    WEN HAOCHENG (Autor:in) / YANG SHENG (Autor:in) / LIN JIAJING (Autor:in) / LIU YUNFEI (Autor:in) / LIU FENG (Autor:in)

    Erscheinungsdatum :

    28.10.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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