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High-altitude long-endurance unmanned aerial vehicle wing suitable for single-wing layout

A long-endurance, unmanned aerial vehicle technology, applied in the aerospace field, can solve problems such as poor performance of high-speed laminar airfoils, and achieve the effects of increasing lateral stability, reducing the range of influence, and improving lift-to-drag ratio

Inactive Publication Date: 2020-08-07
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The embodiment of the present application aims at the existing technology and provides a high-altitude long-endurance UAV wing suitable for the layout of the lower monoplane, which solves the defect of poor performance of the existing high-speed laminar flow airfoil

Method used

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  • High-altitude long-endurance unmanned aerial vehicle wing suitable for single-wing layout
  • High-altitude long-endurance unmanned aerial vehicle wing suitable for single-wing layout
  • High-altitude long-endurance unmanned aerial vehicle wing suitable for single-wing layout

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Experimental program
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Embodiment 1

[0052] This embodiment is designed as figure 1 The shown wing: the leading edge sweep angle of the wing is 9°, the aspect ratio is 17.52, the half-span length of the wing is 8900mm, and the kink is designed at the spanwise position of 2300mm. The chord length of wing root is 2520mm, the chord length of wing tip is 440mm, and the chord length of kink is 1048mm. refer to figure 2 , the airfoil profile is controlled by the wing root, kink and wing tip.

[0053] The dihedral angle within the span of the wing is 1°, and the dihedral angle outside the kink is 0°; the wing has no installation angle.

[0054] The embodiment of this application uses γ-Re θ The transition mode carries out numerical simulation on the wing flow of the present invention, and the Mach number of the calculation state is 0.5, and the flight altitude is 12km, wherein the cruising state corresponds to the state of the maximum lift-to-drag ratio, and the maximum lift-to-drag ratio is 52.3. refer to image...

Embodiment 2

[0058] As a comparison, the inventor γ-Re θThe transition mode numerically simulates the airfoil flow of the present invention and the airfoil flow of the Global Hawk airfoil structure. Wherein the Global Hawk airfoil wing is exactly the same as the wing plane shape of the present invention, that is, the span length, the chord length and the kink position etc. are all consistent. The two wings differ only in airfoil shape. The calculation state Mach number is 0.5, and the flight altitude is 12km.

[0059] refer to Figure 6 The comparison chart of the lift-drag characteristic curves of the two wings, that is, the K-CL curve. As can be seen from the figure, the maximum lift-to-drag ratio of the wing of the embodiment of the present application is obviously greater than that of the Global Hawk airfoil, and the maximum lift-to-drag ratios of the two wings are respectively 52.3 and 46.0, so the wing of the present invention is better than the Global Hawk airfoil The maximum li...

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Abstract

The invention discloses a high-altitude long-endurance unmanned aerial vehicle wing suitable for single-wing layout and relates to the technical field of aerospace. A trapezoidal wing with a kink in the plane shape, the sweepback angle of the front edge is 0-10 degrees, the aspect ratio is 16-20, the kink position is located at the half-span length of 24%-27% bH, and the chord length of the kink position is 0.81-0.82 cA. According to the invention, the surface flow of the wing does not form transverse flow transition, so that the wing has high lift-drag ratio; the accommodating requirements ofan undercarriage and the folding and unfolding mechanism of the undercarriage can be met; the kink design also has the effect of controlling the influence range of wing body interference flow spanwise; the wing sections within the spanwise kink are provided with the upper reverse angles, and the wing sections outside the spanwise kink are not provided with the upper reverse angles, so that on onehand, the height from the wingtip to the ground can be increased, the wingtip is prevented from mopping the ground after the wing is deformed, and on the other hand, the transverse stability can be improved to a certain extent.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a high-altitude long-endurance unmanned aerial vehicle wing suitable for a low-wing layout. Background technique [0002] High-altitude and long-endurance UAVs have the typical characteristics of high flying altitude and long cruising time. They are the first choice for long-term reconnaissance, surveillance and intelligence collection tasks, and can be used as unmanned combat platforms. Therefore, all major aviation countries in the world are very Pay attention to. The U.S. "Global Hawk" UAV is a typical high-altitude long-endurance UAV (such as Figure 5 shown). From the perspective of aerodynamic design, the wing is the core component that determines the aerodynamic characteristics of the aircraft. At present, there is no high-altitude long-endurance UAV product with a low-wing layout in China, and its wing design is out of the question. Contents of the invention [00...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/14
CPCB64C3/14B64U10/25
Inventor 肖良华曹世坤冯文梁张斌姚皆可陈斌
Owner CHENGDU AIRCRAFT INDUSTRY GROUP