The invention discloses a missile-loaded rapid unmanned aerial vehicle which comprises a head body, a fuselage body and a plurality of side wings, the head body is detachably connected with the fuselage body, a bullet head cavity is formed in the head body, a missile body cavity is formed in the fuselage body, and the bullet head cavity and the missile body cavity are communicated to form a cavity used for containing a missile; the side wings are circumferentially distributed on the outer wall of the fuselage body, one end of each side wing is hinged to the outer wall of the fuselage body, the side wings incline towards the tail end of the fuselage body, a plurality of connecting parts are hinged to the tail of the fuselage body and incline towards the nose body, and when the side wings are in an unfolded state, the side wings and the connecting parts are all away from the fuselage body; when the side wings are in the folded state, the side wings and the connecting parts are close to the fuselage body, and locking pieces are arranged between the connecting parts and the corresponding side wings. According to the unmanned aerial vehicle, wind resistance can be reduced in the use state of the unmanned aerial vehicle, and the overall size can be reduced in the transportation process.
本申请公开了一种载弹型快速无人机,其包括机头本体、机身本体以及若干个侧机翼,机头本体与机身本体可拆卸连接,机头本体内部设置有弹头腔室,机身本体内部设置有弹身腔室,弹头腔室与弹身腔室连通形成用于容纳导弹的空腔;若干侧机翼周向分布于机身本体外壁,侧机翼的一端铰接于机身本体外壁,侧机翼朝机身本体的尾端方向倾斜,机身本体的尾部铰接有若干连接部,连接部朝机头本体方向倾斜,当侧机翼呈展开状态时,侧机翼与连接部均远离机身本体;当侧机翼呈收纳状态时,所述侧机翼与连接部均贴近机身本体,连接部与对应的侧机翼之间设置有锁紧件。本申请既能在无人机使用状态下降低风阻,也能在运输过程中缩小整体体积。
Bullet-carrying type rapid unmanned aerial vehicle
一种载弹型快速无人机
2024-08-13
Patent
Electronic Resource
Chinese
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