Unmanned aerial plane launching system and method

A launch system and unmanned aerial vehicle technology, applied in the field of unmanned aerial vehicle systems, can solve problems such as maintenance difficulties, rockets that cannot be reused, and complex structures

Inactive Publication Date: 2007-12-05
XINGYU AVIATION CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These launch methods have the problems of complex structure, high cost of manufacture and use, and difficult maintenance.
For example, the safety measures for the transportation, storage and use of the booster rocket are extremely demanding, which brings gre

Method used

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  • Unmanned aerial plane launching system and method
  • Unmanned aerial plane launching system and method
  • Unmanned aerial plane launching system and method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0017] As shown in Figures 1, 2, and 3, a UAV launch system includes a guide rail system, an ejection system, a braking system, a control system and a power source; the ejection system and the braking system are arranged on the guide rail system ; The control system controls the ejection system and the braking system, and the power source provides energy for the entire system.

[0018] The guide rail system includes a guide rail 1 and a frame body 2, the guide rail 1 is located on the upper surface of the frame body 2, two parallel linear objects extending along the length direction of the frame body 2; the guide rail 1 and the frame body 2 It can be designed as a whole, or it can be divided into at least two sections, and the two connected sections can be folded relative to each other; in order to reduce manufacturing difficulty and facilitate transportation, three sections of guide rails 11, 12, 13 are used in this embodiment, and frame bodies 21, 22, 23 In a foldable form, ...

Embodiment 2

[0024] The difference between this embodiment and the first embodiment is that the elastic body is a large tension spring bundle.

Embodiment 3

[0026] The difference between this embodiment and the first embodiment is that the guide rail 1 and the frame body 2 in the guide rail system are also composed of three sections, but in this embodiment, the guide rail 1 and the frame body 2 are connected in two sections corresponding to Nesting, similar to a sleeve.

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Abstract

The present invention relates to drone, and is especially system and method of launching drone. The drone launching system includes one guide rail system, one ejecting system, one braking system, one control system and one power source. The ejecting system and the braking system are set on the guide rail system, the control system controls the ejecting system and the braking system, the ejecting system includes one power system with one rubber band bundle serving as elastomer to store energy. During being launched, the drone is powered by the elastomer to accelerate in the guide rail. The present invention has low drone launching cost.

Description

technical field [0001] The invention relates to an unmanned aerial vehicle system, in particular to an unmanned aerial vehicle launching system and method. Background technique [0002] Unmanned Aerial Vehicle (UAV) is the abbreviation of "unmanned aircraft", which mainly relies on radio remote control or through autopilot to realize autonomous flight control. It is one of today's high-tech weapons and equipment. It is widely used in many military operations such as battlefield reconnaissance, electronic countermeasures, and air strikes. It is known as the "clairvoyance" and "killer mace" of the modern battlefield. At present, my country's UAV launch system mainly adopts hydraulic, pneumatic, and rocket-assisted launch methods. These launching methods have the problems of complex structure, high cost of manufacture and use, and difficult maintenance. For example, the safety measures for the transportation, storage and use of the booster rocket are extremely demanding, whic...

Claims

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Application Information

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IPC IPC(8): B64F1/04
Inventor 张涪生何望星谭晓东
Owner XINGYU AVIATION CO LTD
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