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A catapult take-off control method for large overload and folding wing UAV

A technology of folding wings and control method, which is applied in the field of UAVs, can solve the problems of stalling, poor anti-interference ability of UAVs, and falling heights, so as to reduce airspeed loss, avoid stalling phenomena, and avoid stalling or falling heights. Effect

Active Publication Date: 2020-09-15
AEROSPACE TIMES FEIHONG TECH CO LTD +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

2. The thrust-to-weight ratio of the aircraft is far less than 1, and the acceleration performance of the UAV is poor
3. The overload impact during the ejection process is likely to cause deviations in the attitude measurement of the UAV
4. After ejection, before the folding wings are fully deployed, the anti-interference ability of the UAV is poor
Therefore, after the UAV is ejected, it is very prone to problems of height drop and stall

Method used

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  • A catapult take-off control method for large overload and folding wing UAV
  • A catapult take-off control method for large overload and folding wing UAV
  • A catapult take-off control method for large overload and folding wing UAV

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Embodiment Construction

[0035] In order to better understand the technical solutions of the present invention, the embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0036] It should be understood that the described embodiments are only some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0037] The terms used in the embodiments of the present invention are only for the purpose of describing specific embodiments, and are not intended to limit the present invention. As used in the embodiments of the present invention and the appended claims, the singular forms "a," "the," and "the" are intended to include the plural forms as well, unless the context clearly dictates otherwise.

[0038] A catapult take-off control method for a ...

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Abstract

The invention provides a ejection take-off control method for a large-overload, folding-wing unmanned aerial vehicle, relates to the technical field of unmanned aerial vehicles, and can make the large-overload, folding-wing unmanned aerial vehicle carry out ejection take-off smoothly, and avoid its occurrence of falling height and stall and other problems that lead to takeoff failure; the method includes S1, ejection takeoff preparation and overload detection; S2, attitude and power control; S3, airspeed and climb rate control; S4, altitude climb control. The technical scheme provided by the invention is suitable for the process of ejection and take-off of the large overload and folding-wing unmanned aerial vehicle.

Description

【Technical field】 [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a catapult take-off control method for a large-overloaded, folding-wing unmanned aerial vehicle. 【Background technique】 [0002] The UAV ejection take-off control is used for the state stability and state transition control of the UAV in the process of large overload and high dynamic ejection. Through the control of the rudder surface and power, the flight state such as the aircraft attitude, airspeed, and altitude can be controlled to achieve A target for the drone to smoothly transition from a pre-ejection state to a normal cruise state. [0003] At present, the catapult take-off method of UAV is mainly based on the catapult take-off method of slide rail. This ejection method is to place the aircraft on a slide rail that forms a certain angle with the ground. The angle is generally set to the trim elevation angle when the aircraft climbs. By releasing the co...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F1/06
CPCB64F1/06B64U70/70
Inventor 卢月亮汤龙成韩松司亮杨红喜王子豪
Owner AEROSPACE TIMES FEIHONG TECH CO LTD
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