Vertical take-off and landing unmanned plane

Abstract

A vertical take-off and landing unmanned plane comprises a body, a motor, a propeller and wings, and further comprises ailerons and vertical fins; the ailerons are in hinged connection with the wings, the number of the vertical fins is three or more, at least one vertical fin is arranged on the upper side of the vertical take-off and landing unmanned plane, at least one vertical fin is arranged on the lower side of the vertical take-off and landing unmanned plane, and the tail edges of at least part of the vertical fins are located at the rear parts of the tail edges of the wings. The tail edges of at least part of the vertical fins are located at the rear parts of the tail edges of the wings, so that when the vertical take-off and landing unmanned plane is vertically placed, the tail edges of the vertical fins are used as an undercart for supporting the vertical take-off and landing unmanned plane. The ailerons are in hinged connection with the wings, so that the vertical take-off and landing unmanned plane flight attitude can be changed by turning the ailerons, vertical takeoff and landing or sky hovering of the vertical take-off and landing unmanned plane can be realized, and high speed horizontal flight of the vertical take-off and landing unmanned plane can be realized.

Description

technical field [0001] The invention relates to an unmanned aerial vehicle, in particular to a vertical take-off and landing unmanned aerial vehicle. Background technique [0002] Due to the advantages of small size and low cost of unmanned aerial vehicles, and with the rapid development of flight control technology, communication technology and electronic technology, the performance and types of unmanned aerial vehicles are constantly increasing, making them widely used in military and civilian fields. application requirements are constantly increasing. [0003] UAVs are generally divided into fixed-wing UAVs and rotary-wing UAVs. [0004] Among them, the fixed-wing UAV is driven by the engine, which generates horizontal thrust parallel to the axis of the fuselage, so that the UAV can fly at high speed in the air. However, since the engine cannot generate lift perpendicular to the axis of the fuselage, the fixed-wing UAV can only obtain lift through the relative motion be...

AI Technical Summary

Problems solved by technology

However, since the engine cannot generate lift perpendicular to the axis of the fuselage, the fixed-wing UAV can only obtain lift through the relative motion between the fixed wing and the air, so as to overcome the gravity of the fixed-wing UAV, the size of the lift and the fixed-wing There is a positive correlation with the relative speed of motion between the air, the greater the relative motion speed, the greater the lift obtained by the fixed-wing UAV

In the prior art, there are two disadvantages in the fixed-wing UAV: ​​first, a long runway is needed to enable the fixed-wing UAV to obtain sufficient horizontal speed so that the fixed-wing UAV can obtain sufficient lift. Take off; Second, the fixed-wing UAV needs to maintain a sufficient flight speed after take-off in order to obtain enough lift to overcome its own gravity

However, since the rotary wing mainly provides lift, the horizontal thrust parallel to the axis of the fuselage obtained by the rotary wing UAV is relatively small, so the horizontal flight speed is relatively slow.

[0006] To sum up, in the prior art, UAVs either need to rely on long runways, and need to maintain sufficient flight speed after take-off; or the horizontal flight speed is relatively slow

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