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A small unmanned aerial vehicle payload launching device

A technology of a small unmanned aerial vehicle and a launching device, applied in the field of unmanned aerial vehicles, can solve the problems of large error and slow load falling time, and achieve the effect of light weight, small size, and convenience for a large number of equipment

Active Publication Date: 2018-11-16
南京壹诺为航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, some launch and delivery devices rely on the gravity of the load itself to launch. This delivery method takes a slow time for the load to fall and has a large error

Method used

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  • A small unmanned aerial vehicle payload launching device

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Embodiment Construction

[0029] Such as figure 1 A kind of small unmanned aerial vehicle load launching device shown, comprises launch tube 12, projectile 14, cover plate 10, negative electrode 13, countersunk screw 5, connector 6 and positive pole rod 7, is provided with in described launch tube 12 Projectile installation groove, the projectile 14 is installed in the projectile installation groove of the launch tube 12, the cover plate 10 is connected on the launch tube 12 through a threaded connection assembly, and the negative electrode 13 is arranged between the projectile 14 and the cover plate 10, the negative pole 13 is in contact with the negative pole on the projectile 14, the negative pole 13 is connected to the cover plate 10 through the countersunk screw 5, the connecting piece 6 is arranged in the cover plate 10, the The lower end of the connector 6 is in contact with the top of the negative pole 13, the upper end of the connector 6 passes through the top of the cover plate 10, a guide gr...

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Abstract

The invention relates to a small unmanned aerial vehicle load launching device which comprises a launching cylinder, a bullet, a cover plate, a negative electrode, a countersunk screw, a connecting piece and a positive electrode rod. A bullet installation groove is formed inside the launching cylinder. The bullet is installed inside the bullet installation groove in the launching cylinder. The cover plate is connected to the launching cylinder through a thread connecting assembly. The negative electrode is arranged between the bullet and the cover plate. The negative electrode makes contact with a negative electrode on the bullet. The connecting piece is arranged inside the cover plate. The lower end of the connecting piece makes contact with the top of the negative electrode. The upper end of the connecting piece penetrates through the top of the cover plate. A guiding groove is formed inside the connecting piece. The positive electrode rod is movably connected into the guiding groove. The tail of the upper end of the positive electrode rod penetrates out from the top of the connecting piece. The semicircular head at the lower end of the positive electrode rod penetrates through the negative electrode to make contact with the positive electrode of the bullet. The small unmanned aerial vehicle load launching device has the advantages of being simple in structure, easy to manufacture, practical and efficient.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a small unmanned aerial vehicle load launching device. Background technique [0002] Small UAVs have the advantages of good concealment performance, strong survivability and outstanding reconnaissance capabilities, and low cost. They are widely used in agricultural plant protection, aerial photography, monitoring, inspection and other fields. [0003] Small UAVs can carry different types of payloads and perform different tasks. For applications such as public security control, anti-terrorism and stability maintenance, drones are required to carry loads such as tear gas, and launch (drop) the load at the right time. At present, some launch and delivery devices rely on the gravity of the load itself to launch. This delivery method takes a slow time for the load to fall and has a large error. [0004] The launching device designed in this project uses a small amou...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F41F1/00
CPCF41F1/00
Inventor 葛贤坤乔治军张先锋陈曙泓罗振宇朱根标宋劲松李磊肖臣
Owner 南京壹诺为航空科技有限公司
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