The invention relates to the field of unmanned aerial vehicle launching devices, in particular to a low-overload telescopic folding-wing unmanned aerial vehicle launching cylinder structure which comprises an outer cylinder, a sealing shell, a telescopic assembly and a gas generation assembly, a piston assembly is slidably connected into the outer cylinder, and an inner cylinder is arranged between the piston assembly and the end of the outer cylinder in a sleeving mode; a limiting structure is arranged between the inner wall of the outer cylinder and the outer wall of the inner cylinder, and the folding wing unmanned aerial vehicle is installed in the inner cylinder in a sliding mode; the sealing shell is connected to the end, away from the inner barrel, of the outer barrel and communicates with the end of the outer barrel. One end of the telescopic assembly is connected with the radial direction of the inner cylinder, and the other end of the telescopic assembly is connected with the radial direction of the sealing shell; the gas generation assembly is used for filling high-pressure and high-temperature gas into the sealing shell, the high-pressure and high-temperature gas enters the outer barrel and then drives the piston assembly to slide in the outer barrel, and then the folding wing unmanned aerial vehicle is driven to be launched. According to the invention, the flexibility of the transport length of the launch canister is improved, the gas production rate tends to be more uniform, and the launch overload peak value is reduced.
本发明涉及无人机发射装置领域,具体涉及一种低过载伸缩式折叠翼无人机发射筒结构,包括:外筒、密封壳体、伸缩组件以及气体发生组件,外筒内滑动连接有活塞组件,活塞组件和外筒的端部之间套设有内筒,且外筒的内壁和内筒的外壁之间设置有限位结构,其中,折叠翼无人机滑动安装于内筒内;密封壳体连接于外筒背离内筒的一端,且其与外筒的端部连通;伸缩组件沿外筒的轴向设置,其一端与内筒的径向连接,其另一端与密封壳体的径向连接;气体发生组件用于为密封壳体充入高压高温气体,高压高温气体进入外筒后驱动活塞组件在外筒内滑动,进而驱动折叠翼无人机发射。本发明提升了发射筒运输长度的灵活性,产气速率更趋均匀,降低了发射过载峰值。
Low-overload telescopic folding wing unmanned aerial vehicle launch canister structure
一种低过载伸缩式折叠翼无人机发射筒结构
2025-05-13
Patent
Electronic Resource
Chinese
IPC: | B64U |
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