Folded launching and withdrawing device for unmanned aerial vehicle

Abstract

The invention discloses a folded launching and withdrawing device for an unmanned aerial vehicle. The folded launching and withdrawing device comprises a base, a folded beam, a launching frame, a launching air cylinder, a traction cable, winch rollers and a pulley set. The tail end of the folded beam is hinged to the base, and the launching air cylinder is fixedly arranged at the end of an inner cavity of the folded beam. The two winch rollers are arranged at the end of the folded beam. The two ends of the traction cable connected with the launching frame are connected with the two winch rollers respectively in a winding mode along a traction line formed by the pulley set. The folded launching and withdrawing device is easy to store and hide after being folded, and is convenient to carry and transport flexibly, a slide is long after unfolding, launching force is large, high controllability is achieved, launching and withdrawing are integrated, fast and continuous launching and withdrawing cross work can be carried out, the large launching type application range is achieved, the device adapts to all carrier-based and vehicle-mounted maneuvering modes, operating can be maintained through a low-power fuel engine or motor, and other guarantees are not needed.

Description

technical field [0001] The invention relates to the field of aviation machinery, in particular to a foldable unmanned aerial vehicle ejection recovery device. Background technique [0002] At present, the known short-distance assisted take-off methods of fixed-wing UAVs include elastic ejection, hydraulic ejection, liquid-pneumatic mixed ejection, rocket-assisted take-off, etc.; Landing and water landing, salvage and recovery, etc. [0003] The elastic catapult has a simple structure and can be used to eject small and miniature fixed-wing UAVs for model aircraft or demonstrations. Due to the limitations of its ejection power, model and control capabilities, the short range and low load of the UAV are determined. characteristics, so the elastic ejection basically has no practical value. [0004] Hydraulic catapult, liquid-pneumatic hybrid catapult and other methods have high power and good controllability, and are suitable for medium and long-range fixed-wing UAV catapult t...

AI Technical Summary

Problems solved by technology

Due to the large length, wingspan and total weight of this type of UAV, in order to ensure a good and stable aerodynamic state during take-off, and taking into account the total load, structural strength, and connection strength of the airframe, airborne equipment, and weapons and ammunition, etc. Factors, the ejection acceleration should not be too high. Therefore, in order to achieve the required separation speed, this type of ejection device generally adopts a whole rigid ejection chute with a large length, and the ejection chute with a large length is very important for the storage and transportation of a complete set of equipment. bring a lot of inconvenience

[0005] In addition to the disadvantages of infrared exposure, the rocket-assisted take-off method is relatively complicated to operate and has certain risks

UAVs with large differences in types and loads often need to be equipped with different types of booster ammunition, which creates more and more complex service

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