The invention relates to the field of unmanned aerial vehicles, in particular to an ejection unmanned aerial vehicle structure which comprises an ejection cavity and an unmanned aerial vehicle, and the ejection cavity comprises a gun barrel, a guide rail and an ejection plate; the unmanned aerial vehicle comprises a shell, a folding wing assembly, a holder assembly and a signal assembly, the shell comprises an upper cavity and a lower cavity, and a plurality of concave positions and notches are correspondingly distributed in the side wall of the upper cavity and the side wall of the lower cavity; the problems that an unmanned aerial vehicle is prone to overturning and inclining in the take-off process, and ejection energy storage is insufficient due to the fact that the folding space of rotor blades of the unmanned aerial vehicle is too large, or an ejection device matched with the unmanned aerial vehicle is too large in specification and not easy to carry are solved. The energy consumption of the unmanned aerial vehicle in the takeoff stage is saved; the ejection direction of the unmanned aerial vehicle is limited; the overall layout of the unmanned aerial vehicle is compact and stable; and the size of the ejection cavity matched with the unmanned aerial vehicle shell is reduced, so that the effects of reducing the structural weight and enhancing the structural stability and the signal transmission stability are achieved.
本发明涉及无人机领域,更具体地,涉及一种弹射无人机结构,其中,包括弹射腔和无人机,所述弹射腔包括炮筒、导轨、弹出板;所述无人机包括壳体、折叠翼组件、云台组件和信号组件,所述壳体包括上腔体和下腔体,所述上腔体的侧壁和所述下腔体的侧壁对应分布若干个凹位和凹口;用于解决无人机在起飞过程中易出现翻转、倾斜的问题,以及无人机的旋翼桨叶折叠空间过大,导致弹射蓄能不足或是适配无人机的弹射装置规格过大,不易携带的问题;节省无人机在起飞阶段的能耗;限定无人机的弹射方向;实现无人机整体布局的紧凑和稳定;以及减小与无人机壳体适配的弹射腔的大小,实现减轻结构重量的同时,加强结构稳定性和信号传递稳定性的效果。
Ejection unmanned aerial vehicle structure
一种弹射无人机结构
2024-07-26
Patent
Electronic Resource
Chinese
IPC: | B64U |
Ejection device, unmanned aerial vehicle and ejection method
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