Laminated plate aircraft skin with flow control and deicing prevention functions

A technology of flow control and aircraft skin, applied in deicing devices, aircraft parts, layered products, etc., can solve the problems of single function of laminated aircraft skin, difficulty in stably installing plasma actuators, etc., and delay stall , Increase the maximum lift coefficient, reduce the effect of differential pressure resistance

Inactive Publication Date: 2013-03-27
COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problem that the aircraft skin of the laminated board has a s

Method used

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  • Laminated plate aircraft skin with flow control and deicing prevention functions
  • Laminated plate aircraft skin with flow control and deicing prevention functions
  • Laminated plate aircraft skin with flow control and deicing prevention functions

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Embodiment Construction

[0018] The manufacture and application of the present invention will be described in further detail below in conjunction with the accompanying drawings, but it is not used as a basis for any limitation of the present invention.

[0019] A laminated aircraft skin with flow control and anti-icing functions, comprising glass fiber layers (2) and aluminum alloy layers (1), the glass fiber layers (2) and aluminum alloy layers (1) alternate with each other; the skin The surface is provided with an insulating material layer (4) and an electrode layer. The electrodes are divided into upper and lower layers. The two layers are respectively located on both sides of the insulating material layer (4) and are distributed asymmetrically. The upper electrode layer (3) is exposed to the air. , connected to an AC power supply, the lower electrode layer (5) is located under the insulating material layer (4) and grounded.

[0020] The electrode layer (3, 5) is made of copper sheet or aluminum al...

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PUM

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Abstract

The invention discloses a laminated plate aircraft skin with lift augmentation, resistance reduction, flow control and deicing prevention functions. The laminated plate aircraft skin comprises a glass fiber layer (2) and an aluminum alloy (1), wherein the glass fiber layer (2) and the aluminum alloy (1) are alternative; the surface of the skin is provided with an insulating material layer (4) and an electrode layer; the electrode layer is divided into an upper layer and a lower layer; the upper layer and the lower layer are respectively positioned on two sides of the insulating material layer (4) and are asymmetrically distributed; the upper electrode layer (3) is exposed in air and is connected with an alternating current power supply; and the lower electrode layer (5) is positioned below the insulating material layer (4) and is grounded. The laminated plate aircraft skin can be directly applied to aircraft manufacturing engineering, cannot be damaged by high-speed airflow and cannot bring parasite drag due to the damage of the original pneumatic shape. The deicing prevention function is realized by utilizing plasma heating on air and the pulse expansion wave function, the flow separation can be effectively controlled, the stall is delayed, the highest lift coefficient is increased, and the pressure difference resistance is reduced.

Description

technical field [0001] The invention relates to a laminated aircraft skin with flow control functions such as lift increase and drag reduction, and anti-icing functions, and belongs to the field of aircraft aerodynamic design and structural design. Background technique [0002] The fiber metal laminate (Glare) skin (hereinafter referred to as laminate) made of glass fiber and metal alternately stacked has been applied to the Airbus A380, as shown in the attached manual figure 1 As shown, it has obvious advantages in terms of tensile strength, crack growth characteristics, and weight reduction compared with traditional metal skins. However, this skin does not have additional functions such as improving aircraft aerodynamic performance and anti-icing. [0003] Install the plasma exciter on the surface of the aircraft, as attached to the manual figure 2 As shown, the flow separation can be suppressed, the stall can be delayed, so as to achieve the purpose of increasing lift ...

Claims

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Application Information

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IPC IPC(8): B64C1/12B64D15/12B64C23/04B32B15/04B32B17/12B32B27/34B32B27/38B32B27/30
CPCB32B15/20B32B17/061
Inventor 王光秋薛帮猛岳广全
Owner COMAC
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