Vertical take-off and landing unmanned aerial vehicle with vectored thrust duct engines

A technology of vector thrust and vertical take-off and landing, which is applied in the direction of vertical take-off and landing aircraft, unmanned aircraft, landing gear, etc. Achieve the effect of reducing dependence, good stability and high flight speed

Active Publication Date: 2018-05-04
SHENYANG AEROSPACE UNIVERSITY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The existing UAVs also have the following problems: 1. Fixed-wing UAVs are generally limited by the take-off and landing sites; 2. Although the multi-rotor UAVs have relatively low restrictions on the take-off and landing sites, they cannot Satisfies the conditions for fast flight of drones and poor maneuverability

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  • Vertical take-off and landing unmanned aerial vehicle with vectored thrust duct engines
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  • Vertical take-off and landing unmanned aerial vehicle with vectored thrust duct engines

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Embodiment Construction

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention. For those skilled in the art, other drawings can also be obtained according to these drawings without any creative effort.

[0023] It should be noted that the ducted engine with vector thrust used in the present invention is a high-efficiency vector thrust ducted fan engine invented by Xing Yuxin and Lan Jian of Dalian University, refer to patent 2016203119750.

[0024] With reference to the accompanying drawings, a vertical take-off and landing UAV with a vector thrust ducted engine comprises a fuselage 1, a wing 2, a vertical tail 3, a roller 4, a vector thrust ducted engine 5, a winglet 6, an auxi...

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Abstract

The invention discloses a vertical take-off and landing unmanned aerial vehicle with vectored thrust duct engines. The unmanned aerial vehicle includes a vehicle body, wings and a vertical tail are separately fixedly installed at the middle and the tail of the vehicle body, the tail ends of the wings are provided with wingtips, vectored thrust duct engines are installed below the wings, and the vertical tail and the wingtips are provided with take-off and landing buffering mechanism. The vertical take-off and landing unmanned aerial vehicle with the vectored thrust duct engines uses the take-off and landing buffering mechanism to vertically take off and land, the flight speed of fixed wing unmanned aerial vehicle is possessed on the one hand, the vertical take-off and landing unmanned aerial vehicle with the vectored thrust duct engines can vertically take off and land and hang in the air like a rotor unmanned aerial vehicle, and the dependency of the unmanned aerial vehicle for sitesand runways is greatly reduced.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicle manufacturing, in particular to a vertical take-off and landing unmanned aerial vehicle with a vector thrust ducted engine. Background technique [0002] Manned aircraft is not only expensive, but also requires long-term training of pilots, which greatly increases the cost. UAV is an unmanned aircraft. Compared with manned aircraft, UAV has incomparable and irreplaceable advantages. The cost of UAV is low, because it is unmanned, it can do more dangerous maneuvers, and it will not cause casualties to pilots. [0003] The existing UAVs also have the following problems: 1. Fixed-wing UAVs are generally limited by the take-off and landing sites; 2. Although the multi-rotor UAVs have relatively low restrictions on the take-off and landing sites, they cannot Satisfies the conditions for fast flight of drones and poor maneuverability. [0004] Therefore, the development of an unmanned aerial ve...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C29/02B64C39/02B64C25/58
CPCB64C25/58B64C29/02B64C39/024B64U50/14B64U2201/20
Inventor 徐光延孟亭磊
Owner SHENYANG AEROSPACE UNIVERSITY
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