Anti-icing device

A technology of anti-icing device and anti-icing system, which is applied in the direction of de-icing device, transportation and packaging, aircraft parts, etc., can solve problems such as adverse effects on aerodynamic performance, and achieve the effects of improving separation control ability, simple structure and reducing aircraft resistance.

Active Publication Date: 2021-06-18
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the existing scheme of using compressed air source or synthetic jet to set air blowing downstream of the thermal protection area of ​​the aerodynamic surface, the selection of the air blowing position is

Method used

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Examples

Experimental program
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Example Embodiment

[0028] Example 1

[0029] An anti-ice device, such as figure 1 As shown, the anti-refrigeration system 2 is included in the aerodynamic leading edge 1, and the micropores 4 are formed on the skin of the anti-ice system 2 downstream, and the micropores 4 are formed, and microporous skin 3 is formed; in the microporous skin 3 At least one air tank 6 is provided below; further comprising the suction device 7, the suction pipe 8 extends into the air tissue 6, the exhaust pipe 9 of the suction device 7 connects the exhaust port on the wing 10. The suction device 7 can be a gas pump.

[0030] Among them, the anti-refrigeration system 2 is a conventional electric heating, hot and ice-free, mechanical anti-ice system, the anti-refrigeration system here is a conventional anti-oil system, which is not described here. The microporous skin 3 is disposed on the wing of the anti-ice system downstream, mainly in order to collect the anti-ice system 2 anti-reflection, overflow water formed by ice...

Example Embodiment

[0035] Example 2

[0036] The present embodiment differs from the first embodiment in that the anti-ice system 2 is no longer provided in the present embodiment, but the microporous skin is provided on the winding surface of the wing.

[0037] Specifically, such as image 3 As shown, the microporous skin 3 is extended to the pneumatic leading edge, and different air tanks and extravasive pipes can be divided according to the needs. image 3In this embodiment, a gas tank 6 is provided downstream of the pneumatic leading edge 1, which is equipped with a suction conduit 8, and a gas tab 6 is provided at a pneumatic leading edge, a suction pipe 8, and two The suction conduit 8 has a plurality of branches to facilitate increasing the efficiency of suction. Of course, the amount of gas tank and the suction pipe cannot be used as a limitation of the invention, in practice, in the drawing of the present embodiment, the microporous skin and airtight tank are set in the drawings of the presen...

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Abstract

The invention is applicable to the technical field of aircraft anti-icing and deicing, and provides an anti-icing device which is characterized in that an anti-icing system is arranged at a pneumatic leading edge, micropores are partially or completely formed in a skin of a downstream wing of the anti-icing system, and a micropore skin is formed; at least one airtight cabin is arranged below the microporous skin; the aircraft further comprises a suction device, an air suction pipeline of the suction device extends into the airtight cabin, and an exhaust pipeline of the suction device is connected with an exhaust port in a wing. Micropores in the micropore skin can effectively'suck 'a turbulent boundary layer, can maintain most laminar boundary layers of the wing, can reduce the resistance of the aircraft and improve the separation control capability of a pneumatic surface, so that the fuel economy of the aircraft is improved, and the requirements of artificial laminar control and overflow water control are met at the same time by adopting one set of system; the deicing device does not need additional air supply, is simple in structure, can be modularly implemented, and can be conveniently applied to light aircrafts and unmanned aerial vehicle systems.

Description

technical field [0001] The invention relates to the technical field of aircraft anti-icing, in particular to an anti-icing device. Background technique [0002] Icing is one of the main causes of aircraft flight accidents. Icing on the leading edge of the wings and tail of the aircraft will lead to increased airfoil resistance, decreased lift, reduced critical angle of attack, and deterioration of maneuverability and stability, resulting in Serious flight accidents have received widespread attention and research. According to the different forms of energy used in anti-icing, it can be divided into mechanical anti-icing systems, electric pulse anti-icing systems, liquid anti-icing systems, hot air anti-icing systems and electric thermal anti-icing systems. The program is currently widely used. [0003] Anti-icing systems focus on aerodynamic surfaces directly impacted by droplets, such as the leading edge of an airfoil, but in some cases, such as high water content in cloud...

Claims

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Application Information

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IPC IPC(8): B64D15/04B64D15/12B64D15/16
CPCB64D15/04B64D15/12B64D15/16
Inventor 胡站伟丁亮易贤赵献礼
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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