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Rotary launching device and launching method of unmanned aerial vehicle

A technology for unmanned aerial vehicles and launching devices, which is applied in the field of rotating launching devices for unmanned aerial vehicles. It can solve problems such as restrictions on the application of unmanned aerial vehicles and weight restrictions on unmanned aerial vehicles, so as to meet the launch height and safety requirements and reduce support requirements. , the effect of small overload

Pending Publication Date: 2021-02-02
江西洪都航空工业股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] For the hand-throwing take-off method, it is conceivable that the weight of this type of UAV is limited by the human body capacity, usually the maximum will not exceed 10kg, which seriously limits the application of UAVs

Method used

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  • Rotary launching device and launching method of unmanned aerial vehicle
  • Rotary launching device and launching method of unmanned aerial vehicle

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Experimental program
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Embodiment 1

[0030] figure 1 It is a rotating launching device of the present invention. The present embodiment provides a rotating launching device for an unmanned aerial vehicle, including a launching device base 1, a rotating column 3, a cantilever beam 4, and a launch hanger 7; one end of the rotating column 3 Rotation is installed on the launching device base 1, and the other end is connected with the cantilever beam 4; the end of the other end of the cantilever beam 4 is equipped with a launch hanger 7 for hanging and launching the unmanned aerial vehicle. The launcher base 1 is built with a damper 2; it is used to brake the rotating column 3 rotating at high speed.

[0031] In this embodiment, the unmanned aerial vehicle power system is started, which drives the rotating column 3 and the cantilever beam 4 to rotate. When the tangential speed of the unmanned aerial vehicle reaches a stable flight speed, at the set rotation angle position, the launch hanger 7 is released. Drone const...

Embodiment 2

[0043] This embodiment provides a method for launching an unmanned aerial vehicle in rotation, using the launching device described in Embodiment 1, the launching method:

[0044] Mount the unmanned aerial vehicle on the launching rack 7, start the power system of the unmanned aerial vehicle 8; drive the unmanned aerial vehicle 3, the cantilever beam 4 and the rotating column 3 to rotate at a high speed under the action of the unmanned aerial vehicle 3 power system;

[0045] When the rotational tangential speed of the UAV reaches a stable separation speed, the launching pylon 7 releases the constraint on the UAV, and the UAV 3 flies in the direction of the tangential speed at the moment of unlocking.

[0046] After the UAV senses the specified tangential acceleration, it sends a shell separation command to the rotary launcher, and the UAV separates after the rotary launcher responds to the command.

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Abstract

The invention provides a rotary launching device of an unmanned aerial vehicle. The rotary launching device comprises a launching device base, a rotary stand column, a cantilever beam and a launchinghanging frame. A problem that at present, unmanned aerial vehicles launch in complex land-based environments or narrow spaces such as ships and warships is solved, and application of various unmannedaerial vehicles on the sea is greatly promoted.

Description

technical field [0001] The invention belongs to the field of unmanned aerial vehicles, and in particular relates to a rotating launching device for unmanned aerial vehicles Background technique [0002] The launch system is an important functional system of UAVs, and it is a necessary technical guarantee to meet the various needs of UAVs such as maneuverability and high survivability. Common UAV launch technologies mainly include rocket-assisted launch, catapult take-off, ground roll take-off, air launch, hand-throwing launch, etc. The main feature is to use external force to accelerate the drone from 0 speed (except for air launch) to Process with stable flight speed. In this acceleration process, it is usually a linear or quasi-linear acceleration process, which generally requires a certain launch site support, especially the ground roll take-off method. [0003] For the use of rocket-assisted launch, ejection take-off, etc., the requirements for the launch site are simp...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F1/04
CPCB64F1/04B64U70/00B64U10/25
Inventor 欧军刘涛魏树孝韩果杨会林高辉王克强黄训义张鹏王刘星马庆跃吴波胡劲张炜翔阳晶昇
Owner 江西洪都航空工业股份有限公司
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