The invention provides a tilt rotor canard vertical take-off and landing unmanned aerial vehicle. The tilt rotor canard vertical take-off and landing unmanned aerial vehicle comprises a fuselage cabin; the main wings are arranged at the top of the fuselage cabin; the two canards are arranged on the two sides of the nose; the tilting structures are arranged at the two ends of the main wing and the canard respectively; the multiple rotors are arranged at the ends, back on to the fuselage cabin, of the tilting structures correspondingly; the control module comprises a first control unit used for controlling the tilting structure to drive the rotor wing to move to the position parallel to the height direction of the fuselage cabin and controlling to increase the rotating speed of the rotor wing to vertically take off; the second control unit is used for controlling the tilting structure to drive the rotor wings to move to the position parallel to the central axis between the nose and the tail for level flight; and the third control unit is used for controlling the tilting structure to drive the rotor to move to a position parallel to the height direction of the fuselage cabin and controlling the rotor to reduce the rotating speed for vertical landing. The unmanned aerial vehicle has the beneficial effects that the rotor wings are rotated through the tilting structures, so that the unmanned aerial vehicle can obtain large horizontal thrust in the level flight process, and the flight speed is increased.

    本发明提供一种倾转旋翼鸭式垂直起降无人机,包括:机身舱体;主翼,设置于机身舱体顶部;两个鸭翼,设置于机头两侧;多个倾转结构,分别设置于主翼和鸭翼的两端;多个旋翼,分别设置于倾转结构的背向机身舱体的一端;控制模块,包括:第一控制单元,用于控制倾转结构带动旋翼移动至平行于机身舱体高度方向的位置并控制增大旋翼转速垂直起飞;第二控制单元,用于控制倾转结构带动旋翼移动至平行于机头和机尾间中轴线的位置进行平飞;第三控制单元,用于控制倾转结构带动旋翼移动至平行于机身舱体高度方向的位置并控制减小旋翼转速垂直降落。有益效果是本发明通过倾转结构旋转旋翼使得无人机在平飞过程中能够获得较大的水平推力,提高飞行速度。


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    Titel :

    Tilt rotor canard vertical take-off and landing unmanned aerial vehicle


    Weitere Titelangaben:

    一种倾转旋翼鸭式垂直起降无人机


    Beteiligte:
    YU WENGUANG (Autor:in) / ZHANG BINGLEI (Autor:in) / YANG SHUNCHAO (Autor:in)

    Erscheinungsdatum :

    2022-09-23


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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