Universal elastic potential energy mechanical catapult for UAV with propeller rear single string wing

Abstract

The invention discloses a general-purpose elastic potential energy mechanical catapult for a single-wing unmanned aerial vehicle with a rear propeller, which includes a body, an ejection frame assembly, an ejection frame assembly, and an aircraft body structure reinforced ejection assembly fixed at the lower part of the aircraft; the body is equipped with slide rails , a slider is embedded in the slide rail; a catapult switch assembly is installed at the end of the body; a winch is installed at the lower part of the body; a direction-adjustable support frame assembly is installed on both sides of the body; a roller shock absorber holder assembly is installed at the head end of the body; The upper part of the slide block in the rail is connected with the ejection frame assembly; the upper part of the ejection frame assembly is connected with the ejection extension device, and the aircraft is installed on the ejection extension device; the body structure reinforced ejection assembly fit with the ejection extension device is installed at the lower part of the aircraft body. The invention adopts a modular design, which is easy to disassemble and assemble, and is convenient to carry. The ejection expansion device and the body are convenient to be flexibly integrated according to specific conditions, and the adaptability of the catapult to unmanned aerial vehicles and the environment is improved, which can effectively improve the cost-effectiveness of use.

Description

technical field [0001] The invention relates to the field of assisted take-off of fixed-wing unmanned aerial vehicles, in particular to a general-purpose elastic potential energy mechanical catapult for single-wing UAVs with rear propellers. Background technique [0002] At present, many application fields such as military reconnaissance, urban security, and disaster rescue require the intervention and assistance of aircraft. At this stage, UAVs are mainly divided into fixed-wing UAVs and rotary-wing UAVs. Among them, fixed-wing unmanned aerial vehicles are developing towards two extremes, one is larger in size, emphasizing the characteristics of multi-module, high load, and long endurance; the other is smaller in size, emphasizing maneuverability , easy to carry and other characteristics of unmanned aerial vehicles, but small unmanned aerial vehicles with this feature are often designed as aircraft without landing gear (flying wing aircraft) because of their carrying chara...

AI Technical Summary

Problems solved by technology

Among them, fixed-wing unmanned aerial vehicles are developing towards two extremes, one is larger in size, emphasizing the characteristics of multi-module, high load, and long endurance; the other is smaller in size, emphasizing maneuverability , easy to carry and other characteristics of unmanned aerial vehicles, but small unmanned aerial vehicles with this feature are often designed as aircraft without landing gear (flying wing aircraft) because of their carrying characteristics, or their take-off surface is often in the wild environment, unable to Take off with conventional landing gear

In addition, in terms of aircraft: due to the multi-tasking requirements of the above-mentioned small unmanned aerial vehicles, the quality of the whole machine has an upward trend, which has brought many limiting factors to the successful manual throwing take-off; in terms of operators, the design of small unmanned aerial vehicles One of the purposes of the aircraft is portability. Under the limitation of manual throwing and take-off caused by objective factors, the portability, ease of operation and superiority of the tool's cost-effectiveness are particularly important.

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