The invention provides an aerodynamic optimization hybrid multirotor, comprising a fuselage, at least one undercarriage, a fuel engine, an installation platform, power rotors, a power-driven rotor mechanism and an aerodynamic optimization mechanism, wherein the fuselage is provided with an upper surface, a lower surface and a first cavity; the undercarriage is fixed to the lower surface of the fuselage; the installation platform is semi-enclosed and is fixed to the lower surface of the fuselage and used for installing the fuel engine, and a second cavity connected with the first cavity is formed; the power rotors are used for being driven by the fuel engine to rotate to enable the multirotor to fly, arranged on the output shaft of the fuel engine and positioned in the first cavity or the second cavity; the power-driven rotor mechanism is used for receiving a far-end first control signal to adjust the flight attitude of the multirotor; the aerodynamic optimization mechanism is used for receiving a far-end second control signal to eliminate reverse twist during the flight of the multirotor and arranged on the outer wall of the installation platform. By implementing the aerodynamic optimization hybrid multirotor, the fuel engine and the power rotors are adopted, the aerodynamic optimization hybrid multirotor has the characteristics of simple structure, stable flight, easy operation and the like, and the carrying capacity, the battery life, the cruising speed, the size and the structure are greatly improved.


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    Titel :

    Aerodynamic optimization hybrid multirotor


    Beteiligte:
    ZHANG XIN (Autor:in) / WANG SONG (Autor:in) / LI XUN (Autor:in) / DUN WENQIANG (Autor:in) / HUANG RONGHUI (Autor:in) / CHEN WANLI (Autor:in) / YAO SENJING (Autor:in) / PEI HUIKUN (Autor:in) / ZHOU WEICAI (Autor:in)

    Erscheinungsdatum :

    2015-08-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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