High-stability double-tail-support vertical annular wing unmanned aerial vehicle

A ring-shaped wing, high-stability technology, used in unmanned aerial vehicles, motor vehicles, heat-reducing structures, etc., can solve unfavorable precision or more demanding tasks, weak stability and wind resistance, and large take-off weight of drones and other problems, to achieve the effect of improving flow field distribution, optimizing structural performance, and excellent flight stability

Pending Publication Date: 2019-09-10
ZHENGZHOU UNIVERSITY OF AERONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the conventional fixed-wing aircraft design method is weak in stability and wind resistance, which is not conducive to achieving higher precision or more demanding tasks. At the same time, in order to improve the range and cruise time, it is necessary to improve the aerodynamic performance of the aircraft.
[0004] The technical problem of the present invention is that the cur

Method used

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  • High-stability double-tail-support vertical annular wing unmanned aerial vehicle
  • High-stability double-tail-support vertical annular wing unmanned aerial vehicle
  • High-stability double-tail-support vertical annular wing unmanned aerial vehicle

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0024] Example 1

[0025] The present invention provides a high-stability dual-tail support vertical annular wing drone. The high-stability dual-tail support vertical annular wing drone includes a fusion fuselage 1, a vertical annular wing 2, and a double tail support 3. Vertical tail 4, flat tail 5, propeller propulsion system 6, control system 7.

[0026] The fusion fuselage 1 is placed in the middle of the lower elliptical wing 22 in a curved surface fusion manner, and can be used for infrared, photoelectric, medical equipment, emergency medicines, etc., and the payload is 8kg.

[0027] The vertical annular wing 2 includes an upper elliptical wing 21 and a lower elliptical wing 22. The upper elliptical wing 21 and the lower elliptical wing 22 are connected at the wing tip to form the annular wing 2; The elliptical wing 21 and the lower elliptical wing 22 adopt NACA series 4-digit airfoil; the upper elliptical wing 21 can adopt the forward-swept method, and the lower elliptical wi...

Example Embodiment

[0032] Example 2

[0033] The difference between Example 2 and Example 1 is: the payload weighs 15 kg; the NACA five-digit airfoil is adopted; the forward sweep angle and the backward sweep angle are 8 degrees.

[0034] The fusion fuselage 1 is placed in the middle of the lower elliptical wing 22 in a curved surface fusion manner, and the load is photoelectric detection equipment or aerial survey monitoring equipment, placed inside the fuselage, and the payload weighs 15 kg.

[0035] The upper elliptical wing 21 and the lower elliptical wing 22 of the vertical annular wing 2 adopt NACA five-digit airfoil; the upper elliptical wing 21 can adopt the forward sweep mode, and the lower elliptical wing 22 can be Adopting the sweep mode, the forward sweep angle and the backward sweep angle are 8 degrees.

[0036] The propeller 63 is installed at the rear end of the propulsion system driving device 62 and adopts a 3-blade propeller.

Example Embodiment

[0037] Example 3

[0038] The difference between embodiment 3 and embodiment 1 is that the payload weighs 20kg, the vertical annular wing adopts a laminar airfoil, the forward sweep angle and the backward sweep angle are 12 degrees, and the propulsion system support frame is set on the lower oval wing. 0.5 times the chord length.

[0039] The fusion fuselage 1 is placed in the middle of the lower elliptical wing 22 in a curved surface fusion manner, the load is laser detection and testing equipment, and it is placed inside the fuselage, and the effective load weighs 20 kg.

[0040] The upper elliptical wing 21 and the lower elliptical wing 22 of the vertical annular wing 2 adopt NACA laminar airfoil; the upper elliptical wing 21 can adopt the forward sweep mode, and the lower elliptical wing 22 can adopt Sweep mode, the forward sweep angle and the backward sweep angle are 12 degrees.

[0041] The propeller propulsion system 6 is composed of a propulsion system support frame 61, a pro...

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Abstract

The invention discloses a high-stability double-tail-support vertical type annular wing unmanned aerial vehicle. The high-stability double-tail-support vertical type annular wing unmanned aerial vehicle comprises a fusion type vehicle body, vertical type annular wings, double tail supports, a vertical tail, a horizontal tail, a propeller propelling system and a control system. The vertical annularwing comprises an upper elliptical wing and a lower elliptical wing; the propeller propelling system comprises a propelling system supporting frame, a propelling system driving device and a propeller; and the control system comprises a rudder, an elevator and ailerons. The unmanned aerial vehicle has excellent wind resistance, the flight resistance of which is improved by more than 8% compared with a conventional layout, and the unmanned aerial vehicle is suitable for high-precision aerial survey aerial photography, mountain forest important material putting and the like and has excellent flight stability.

Description

technical field [0001] The invention relates to the field of design and manufacture of unmanned aerial vehicles, in particular to a highly stable double-tail support vertical ring-wing unmanned aerial vehicle. Background technique [0002] Industrial-grade drones have been widely used in agriculture, forestry and plant protection, geological survey, aerial surveying and mapping, aerial photography, rescue, etc. With the improvement of the accuracy requirements of aerial surveying and aerial photography, the flight stability and wind resistance of drones have been raised. For higher requirements, it is necessary to design a high-stability UAV that can be used for high-precision mapping and shooting to provide platform support. With the development of aviation logistics, emergency rescue, disaster detection and early warning, etc., the valley wind in mountainous areas and severe weather when geological disasters occur all put forward higher requirements for UAVs. UAVs should...

Claims

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Application Information

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IPC IPC(8): B64C39/06B64C25/04B64C3/36
CPCB64C39/062B64C25/04B64C3/36B64U2101/00
Inventor 刘战合张芦田秋丽田博韬王菲郝爱民王菁罗丽红张淦秦国平夏陆林祝令杰
Owner ZHENGZHOU UNIVERSITY OF AERONAUTICS
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