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Vertical take-off and landing tandem wing unmanned aerial vehicle

A technology of vertical take-off and landing and tandem wings, which is applied in the field of unmanned aerial vehicles, can solve the problems of undiscovered patented technology, flight stability and insufficient propulsion, etc., and achieve flexible control of flight status, good layout, and small environmental requirements Effect

Inactive Publication Date: 2016-04-06
天津全华时代航天科技发展有限公司
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, UAVs can be divided into various types according to the structure. The take-off and landing forms are mainly divided into two types: vertical take-off and landing and those that require a runway or ejection. Capable of vertical take-off and landing, however, the existing vertical take-off and landing UAVs often have problems of flight stability and insufficient propulsion in the air
[0003] After a preliminary search, no published patented technology identical to this patent was found

Method used

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  • Vertical take-off and landing tandem wing unmanned aerial vehicle
  • Vertical take-off and landing tandem wing unmanned aerial vehicle
  • Vertical take-off and landing tandem wing unmanned aerial vehicle

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Embodiment Construction

[0019] The present invention will be further described in detail below in conjunction with the accompanying drawings and through specific embodiments. The following embodiments are only descriptive, not restrictive, and cannot limit the protection scope of the present invention.

[0020] A vertical take-off and landing tandem wing UAV, comprising a fuselage 1, a main wing 5, an empennage 9 and a vertical empennage 7, both sides of the middle of the fuselage are symmetrically fixed with main wings, and the rear of the fuselage behind the main wings on both sides Empennages are installed symmetrically on both sides, and a vertical empennage is fixedly installed on the upper end of the rear part of the fuselage.

[0021] In order to effectively control the air running state of the UAV, a main wing aileron 6 whose swing angle is controlled by a motor is hinged at the rear of the main wing, and a tail aileron 6 whose swing angle is controlled by a motor is hinged at the rear of the ...

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Abstract

The invention relates to a vertical take-off and landing tandem wing unmanned aerial vehicle. The vehicle take-off and landing tandem wing unmanned aerial vehicle comprises a vehicle body, main wings, empennages and a vertical empennage, wherein the main wings are symmetrically and fixedly installed on the two sides of the middle of the vehicle body; the empennages are symmetrically and fixedly installed on the two sides of the rear portion of the vehicle body and behind the main wings on the two sides; the vertical empennage is fixedly installed at the upper end of the rear portion of the vehicle body; the upper ends of the main wings and the empennages on the two sides of the vehicle body are each provided with a rotary wing support; a rotary wing is adjustably hinged to the upper end of each rotary wing support; each rotary wing is provided with a drive motor in a driving mode. The layout is good, the self stability is good, the vertical taking-off and landing are achieved, the multiple rotary wings are adopted as control sources, the unmanned aerial vehicle can vertically take off and land, the bearing capacity is high, and the requirement for a take-off site environment is low. The angles of the rotary wings can be controlled, and the rotary wings can work in a tilt angle state, so that the unmanned aerial vehicle is automatically and smoothly switched from one state to another state, and the flying state is conveniently and flexibly controlled.

Description

technical field [0001] The invention belongs to the field of unmanned aerial vehicles, in particular to a vertical take-off and landing tandem-wing unmanned aerial vehicle. Background technique [0002] In recent years, with the gradual maturity of unmanned aircraft technology and the progress of supporting control equipment, it has the feasibility of various technical applications. At present, UAVs can be divided into various types according to the structure. The take-off and landing forms are mainly divided into two types: vertical take-off and landing and those that require a runway or ejection. Capable of vertical take-off and landing, however, the existing vertical take-off and landing drones often have the problems of air flight stability and insufficient propulsion. [0003] After a preliminary search, no published patented technology identical to this patent was found. Contents of the invention [0004] The purpose of the present invention is to overcome the defi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/28
CPCB64C27/28
Inventor 田凯权军胡俊
Owner 天津全华时代航天科技发展有限公司
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