The invention discloses an unmanned aerial vehicle undercarriage buffering structure which comprises supporting rods symmetrically distributed on an unmanned aerial vehicle body, the lower end of each supporting rod is provided with a buffering structure, each buffering structure comprises a hollow metal pipe body, and the upper end of each metal pipe body is connected with the lower end of the corresponding supporting rod in an inserted mode; at least one rod-shaped fastening assembly is arranged between the metal pipe body and the supporting rod, positioning round holes allowing the fastening assemblies to penetrate through are formed in the side wall of the metal pipe body and the side wall of the supporting rod correspondingly, and the sides, away from the unmanned aerial vehicle body, of the positioning round holes in the metal pipe body are connected with guiding long holes parallel to the central axis of the metal pipe body. The width of the guiding long holes is smaller than the diameter of the positioning round holes. Through plastic deformation generated by mutual extrusion between the fastening assembly and the guiding long holes, impact energy generated when the unmanned aerial vehicle touches the ground is absorbed, meanwhile, the guiding long holes also play a role in guide limiting and buffering, the impact force is limited not to exceed a specific value, and the unmanned aerial vehicle undercarriage buffering structure is suitable for various common undercarriage structures of the unmanned aerial vehicle.

    本发明公开了一种无人机起落架缓冲结构,包括对称分布在无人机主体上的支撑杆,每一支撑杆的下端设有缓冲结构,缓冲结构包括中空的金属管体,金属管体的上端与支撑杆的下端插接连接,金属管体和支撑杆之间设有至少一个杆状的紧固组件,金属管体与支撑杆的侧壁上均设有可供紧固组件贯穿的定位圆孔,金属管体上的定位圆孔在远离无人机主体的一侧连接设有与金属管体的中轴线平行的导向长孔,导向长孔的宽度小于定位圆孔的直径。本发明通利紧固组件与导向长孔之间相互挤压产生的塑性变形,从而吸收触地时产生的冲击能量,同时,导向长孔也起到导向限位和缓冲的作用,限制冲击力不超过特定值,适用于无人机常见的多种类型的起落架构型。


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    Titel :

    Unmanned aerial vehicle undercarriage buffering structure


    Weitere Titelangaben:

    一种无人机起落架缓冲结构


    Beteiligte:
    YAN WEITIAN (Autor:in) / REN XUEFENG (Autor:in)

    Erscheinungsdatum :

    2022-01-07


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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