Tilting ducted unmanned aerial vehicle

A UAV and ducted technology, applied in the field of UAVs, can solve the problems of inability to achieve normal takeoff and landing, small mission radius, high takeoff speed, etc.

Pending Publication Date: 2021-07-23
AVIC (CHENGDU) UAS CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the high take-off speed required by fixed-wing UAVs, they are highly dependent on the runway and its surrounding environment, and cannot achieve normal take-off and landing in certain environments.
Existing fixed-wing UAVs are difficult to deploy in places with limited take-off and landing sites such as warships
Unmanned helicopters can take off and land flexibly on a small site, and can hover over the target for a long time, but they have the disadvantages of slow flight speed and small mission radius

Method used

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Embodiment Construction

[0025] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0026] In order to enable those skilled in the art to better understand the solution of the present invention, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0027] Please refer to Figure 1 to Figure 5 , figure 1 Schematic diagram of the structure of the tilting duct unmanned aerial vehicle provided by the present invention; figure 2 for figure 1 The front view of t...

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Abstract

The invention discloses a tilting ducted unmanned aerial vehicle, which comprises a fuselage, side wings are arranged in the middle of the fuselage, a horizontal empennage and a vertical empennage are arranged on the rear portion of the fuselage, tilting ducted fans are arranged on the side wings and the horizontal empennage, and a driving device connected with the tilting ducted fans is arranged on the fuselage. Tilting ducted fans are arranged on side wings and a horizontal tail wing of the tilting ducted unmanned aerial vehicle. During take-off and landing, the tilting ducted fans are perpendicular to the airfoil, airflow flows downwards to provide lift force, so that the tilting ducted unmanned aerial vehicle realizes vertical take-off and landing, and the requirements of the unmanned aerial vehicle on running and the surrounding environment are reduced. During level flight, the tilting ducted fans are parallel to airfoils, airflow flows backwards to provide thrust, the side wings of the unmanned aerial vehicle generate lift force, it is guaranteed that the tilting ducted unmanned aerial vehicle can fly at a high speed, and the tilting ducted unmanned aerial vehicle has the advantages of being high in speed and large in task radius.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a tilting duct unmanned aerial vehicle. Background technique [0002] Fixed-wing UAV has the advantages of fast speed and large mission radius, and its actual combat effect is remarkable. However, due to the high take-off speed required by fixed-wing UAVs, they are highly dependent on the runway and its surrounding environment, and cannot achieve normal take-off and landing in certain specific environments. Existing fixed-wing UAVs are difficult to deploy in places with limited take-off and landing sites, such as warships. Unmanned helicopters can take off and land flexibly in a small space, and can hover over the target for a long time, but they have the disadvantages of slow flight speed and small mission radius. [0003] Therefore, how to provide an unmanned aerial vehicle with low environmental requirements, high speed and large mission radius is a technica...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C29/00B64C5/02B64C5/06B64D27/24B64D27/10B64D27/04
CPCB64C29/00B64C5/02B64C5/06B64D27/24B64D27/10B64D27/04B64U10/25
Inventor 李屹东陈安强田浩邓捷王兵
Owner AVIC (CHENGDU) UAS CO LTD
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