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UAV Catapult System

A technology of unmanned aerial vehicle and slewing mechanism, which is applied in the direction of launch/drag transmission device, etc., can solve the problems of unmanned aerial vehicle take-off, aircraft damage, and narrow application range of ejection device, and achieves simple structure and service life. Long, precise firing effect

Active Publication Date: 2022-02-11
YANSHAN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing UAV ejection systems are in various forms, and there are many application methods such as pneumatic ejection, electromagnetic ejection, and spring ejection; moreover, the scope of application of existing ejection devices is relatively narrow. , ejection speed, terrain and release device failure and other factors lead to damage to the aircraft, which cannot well meet the requirements for UAV take-off

Method used

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Embodiment Construction

[0026] Such as figure 1 As shown, the UAV ejection system of the present invention includes a traction mechanism 100 , a leveling mechanism 200 , a clamping mechanism 300 , a pitch mechanism 400 , a guiding mechanism 500 , a braking mechanism 600 and a turning mechanism 700 . The entire device is powered by a vehicle power supply or a pump station, which facilitates the transportation of various vehicles.

[0027] Such as figure 2 As shown, the traction mechanism 100 includes a variable frequency motor 101 , a traction rope 102 , a guide wheel 103 , an electromagnet 104 , a buffer spring 105 , a reel wheel 106 and a traction trolley 107 . The frequency conversion motor 101 and the reel wheel 106 are coaxially connected and fixed on the slewing mechanism 700, the traction rope 102 on the reel wheel 106 bypasses the guide wheel 103 fixed on the guide rail 501 and is connected with the buffer spring 105, and the buffer spring 105 is connected with the traction The dolly 107 is...

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Abstract

The invention relates to an unmanned aerial vehicle ejection system, comprising a clamping mechanism, a traction mechanism, a pitching mechanism, a slewing mechanism, a leveling mechanism, a guiding mechanism and a braking mechanism. When the unmanned aerial vehicle of the present invention is in the static stage and the ejection stage, the positioning balls in the lower rotating rod enter into the ball clamping holes under the action of the spring force of the lower rotating rod spring, so as to realize the locking of the guide wheel release device; During the release stage, the hook of the traction trolley slides in the hook groove, and the lower lever spring is compressed under the action of the wire rope, so that the positioning ball in the lower lever is separated from the ball clamping hole, and the guide wheel release device is turned clockwise to realize The release of the drone. The invention can realize the all-round and multi-angle launching of the unmanned aerial vehicle, so that the launching of the unmanned aerial vehicle is more accurate.

Description

technical field [0001] The invention belongs to the field of aviation equipment, and in particular relates to an unmanned aerial vehicle ejection system, which can ensure rapid and stable take-off of the unmanned aerial vehicle under complex landforms, and can also be combined with a vehicle-mounted transportation platform to realize safe transportation on roads and railways. Background technique [0002] At present, the take-off of small and medium-sized drones is limited by space, and ejection devices are often used to assist the take-off of the aircraft. Existing UAV ejection systems are in various forms, and there are many application methods such as pneumatic ejection, electromagnetic ejection, and spring ejection; moreover, the scope of application of existing ejection devices is relatively narrow. , Ejection speed, terrain and release device failure and other factors lead to damage to the aircraft, which cannot well meet the requirements for UAV take-off. Contents o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F1/06
Inventor 赵静一张亚卿张启星王留根张立轩石玉龙
Owner YANSHAN UNIV
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