Vertical take-off and landing UAV with vector thrust ducted engine

A vector thrust, vertical take-off and landing technology, which is applied in vertical take-off and landing aircraft, unmanned aircraft, landing gear, etc., can solve the problems of limited take-off and landing sites, poor maneuverability, and the inability to meet the rapid flight of drones, etc. Achieve the effect of reducing dependence, good stability and high flight speed

Active Publication Date: 2022-02-01
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 UAV with vector thrust ducted engine
  • Vertical take-off and landing UAV with vector thrust ducted engine
  • Vertical take-off and landing UAV with vector thrust ducted engine

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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 a vector thrust ducted engine, comprising a fuselage, a wing and a vertical tail are respectively fixed in the middle and the tail of the fuselage, and a winglet is provided at the end of the wing. , a vector thrust ducted engine is installed under the wing, the vertical tail and the winglet are provided with a take-off and landing buffer mechanism; the UAV performs vertical take-off, landing and parking through the take-off and landing buffer mechanism, On the one hand, it has the flying speed of fixed-wing drones, and on the other hand, it can perform vertical take-off, landing and hovering like rotary-wing drones, which greatly reduces the drone's dependence on the venue runway.

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 Patents(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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