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Pneumatic catapult-assisted take-off device and method used for unmanned plane

A technology of air pressure and air storage tank, which is applied in the direction of launch/drag transmission device, etc., can solve the problems of low ejection end speed of the catapult, limit the popularization and use of the catapult, and low ejection weight of the catapult device, so as to improve the ejection efficiency and reduce the maintenance. Cost, convenient transportation effect

Inactive Publication Date: 2016-04-06
SHAANXI AIRCRAFT CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

Disadvantages are: short service life of the rubber bands; low ejection weight of the ejection device; low ejection end velocity of the catapult; high maintenance costs; high risk during the take-off phase
Due to the above characteristics, the promotion and use of catapults in UAVs is limited, and the scope of application is small

Method used

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  • Pneumatic catapult-assisted take-off device and method used for unmanned plane
  • Pneumatic catapult-assisted take-off device and method used for unmanned plane

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Embodiment Construction

[0022] combined with figure 1 , the air pressure catapult take-off device of the present invention comprises an air compressor 1, an air storage tank 2, an action cylinder 3, a locking device 10, a guide rail 16, a steel cable 13, a block of pulleys and a guide rail block, wherein the block of pulleys includes a block of drive pulleys and a block of guide pulleys, The drive pulley set is composed of the first pulley 4, the second pulley 5 and the L-shaped ejector rod, and the guide pulley set is composed of the third pulley 6 and the fourth pulley 7 and is fixedly connected with the launch frame; wherein the compressor 1 is connected with the gas storage The tank 2 is connected and can pressurize the gas storage tank 2, one end of the action cylinder 3 communicates with the gas outlet of the gas storage tank 2, and the piston rod in the action cylinder 3 is fixedly connected with the L-shaped ejector rod; the steel Cable 13 walks around the third pulley 6 and the fourth pulley...

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Abstract

The invention belongs to the technical field of catapult-assisted take-off of aircrafts and particularly relates to a pneumatic catapult-assisted take-off device and method used for an unmanned plane. Rubber bands are adopted for most existing catapult devices in China, the service life of the rubber bands is short, the catapult weight of the catapult devices is low, the tail end catapulting speed of catapults is low, the maintenance cost is high, and the risk in the take-off stage is high; consequentially, the application and popularization of the catapults in the field of unmanned planes are limited, and the application range is narrow. By the adoption of the pneumatic catapult-assisted take-off device and method used for the unmanned plane, the unmanned plane is made to get rid of the limitation of airport conditions, the service life of an existing catapult is prolonged, and the catapult weight of the catapult is increased.

Description

Technical field [0001] The invention belongs to the technical field of aircraft ejection and take-off, and specifically relates to a device and method for pneumatic ejection and take-off of an unmanned aerial vehicle. Background technique [0002] Most of the existing ejection devices in the country use rubber bands to eject. After pulling apart multiple rubber bands, they are suddenly released to eject the drone into the air. Its disadvantages are: the service life of the rubber band is short; the ejection weight of the ejection device is low; the ejection end speed of the catapult is low; the maintenance cost is high; and the risk during the take-off phase is high. Due to the above characteristics, the promotion and use of catapults in drones is limited, and the scope of application is small. Contents of the invention [0003] The purpose of the present invention is to propose a pneumatic catapult take-off device and method in order to free UAVs from the constraints of ...

Claims

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Application Information

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IPC IPC(8): B64F1/06
CPCB64F1/06
Inventor 朱连伟靳宏斌张龙魏晓明王佰硕陶岸峰陈向东潘伟琳李伟伟
Owner SHAANXI AIRCRAFT CORPORATION
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