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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 current low-speed fixed-wing UAVs used for aerial survey, logistics, and aerial photography have the following key problems: (1) poor flight stability and weak wind resistance; (2) low-speed flight resistance is relatively large ;(3) The take-off weight of the UAV is too large under the same load; (4) Multi-task compatibility
Thereby limiting the greater development of this type of UAV

Method used

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

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Experimental program
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Effect test

Embodiment 1

[0025] A high-stability double-tail vertical ring-wing unmanned aerial vehicle of the present invention, said high-stability double-tail vertical ring-wing UAV includes a fusion fuselage 1, a vertical ring-shaped wing 2, a double tail support 3. Vertical tail 4, horizontal 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 medicine, etc., and the payload is 8kg.

[0027] Described vertical annular wing 2 comprises upper oval wing 21 and lower oval wing 22, and upper oval wing 21 and lower oval wing 22 are connected to form annular wing 2 at wingtip; The elliptical wing 21 and the lower elliptical wing 22 adopt the NACA series 4-digit airfoil; the upper elliptical wing 21 can be swept forward, and the lower elliptical wing 22 can be swept back. The sweep angle is 5 degrees. The...

Embodiment 2

[0033] The difference between embodiment 2 and embodiment 1 is that: the payload weighs 15 kg; the NACA five-digit airfoil is adopted; the forward and backward sweep angles 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, which is 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 the NACA five-digit airfoil; The sweeping method is adopted, and the sweeping angle and the sweeping angle are 8 degrees.

[0036] The propeller 63 is installed on the rear end of the propulsion system driving device 62 and adopts 3 blades.

Embodiment 3

[0038]The difference between Embodiment 3 and Embodiment 1 is that the payload is 20 kg, the vertical ring-shaped wing adopts a laminar airfoil, the sweep angle and the sweep angle are 12 degrees, and the propulsion system support frame is arranged 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, and the load is laser detection and testing equipment, which is placed inside the fuselage, and the payload weighs 20 kg.

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

[0041] The propeller propulsion system 6 is composed of a propulsion system support frame 61, a propulsion system driving device 62 and a propeller 63, and the propulsion system support frame 61 is arranged at the rear end of the fusion type fus...

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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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