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Microporous seepage structure, airplane anti-icing system and airplane

An anti-icing system and microporous technology, applied in aircraft parts, deicing devices, transportation and packaging, etc., can solve the problems of high energy consumption, damage to the aerodynamic shape of the wing, large thermal inertia, etc., and achieve easy use and technical capabilities and the effect of less judgment requirements and low operating energy consumption

Pending Publication Date: 2021-01-08
中电科芜湖通用航空产业技术研究院有限公司 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Disadvantages of thermal anti-icing: relatively large thermal inertia, easy to form icicles behind the heating zone, which disturbs the airflow, low thermal efficiency, and high energy consumption
Disadvantages of mechanical anti-icing: the expansion tube protrudes from the surface of the aircraft skin and destroys the aerodynamic shape of the wing

Method used

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  • Microporous seepage structure, airplane anti-icing system and airplane
  • Microporous seepage structure, airplane anti-icing system and airplane

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] Such as figure 1 As shown, the embodiment of the present application provides a microporous liquid-permeable structure 100 . The microporous liquid-permeable structure 100 includes a first panel 101 , a second panel 102 and a damping membrane 104 .

[0023] Multiple microholes are uniformly arranged on the first panel 101 . The edge of the second panel 102 is attached to the side of the first panel 101 and can be connected by laser welding. A liquid storage chamber is formed between the first panel 101 and the second panel 102, and the liquid storage chamber is used for storing anti-icing fluid. The second panel 102 is provided with an anti-icing liquid inlet 103 for entering the anti-icing liquid into the liquid storage chamber.

[0024] The damping membrane 104 is disposed on the inner wall of the first panel 101 , and the damping membrane 104 covers all micropores on the inner wall of the first panel 101 . The damping diaphragm 104 is a porous diaphragm of the ex...

Embodiment 2

[0027] Such as figure 2 As shown, this embodiment provides an aircraft anti-icing system 200 . The aircraft anti-icing system 200 includes an anti-icing liquid tank 201 , a quantitative pump 202 , a filter 203 and the microporous liquid-permeable structure 100 as described above.

[0028] The anti-icing fluid tank 201 is used to store the anti-icing fluid, and the anti-icing fluid stored in the anti-icing fluid tank 201 should ensure that the aircraft anti-icing system 200 can operate normally for at least about 150 minutes. The size of the anti-icing fluid tank 201 can be adjusted according to requirements.

[0029] The quantitative pump 202 is connected to the anti-icing fluid tank 201 to provide anti-icing fluid with a certain pressure and flow rate for the anti-icing of the fuselage. There may be multiple quantitative pumps 202. In this embodiment, there are two quantitative pumps 202, one as the main pump and one as the auxiliary pump. The flow rate of the quantitativ...

Embodiment 3

[0037] This embodiment provides an aircraft, including the above aircraft anti-icing system 200 . There are multiple microporous liquid-permeable structures 100, among which, the first microporous liquid-permeable structure 100a is bent into the shape of the leading edge of the left wing and arranged on the left wing, and the second microporous liquid-permeable structure 100b is bent into the shape of the right wing The shape of the leading edge is set on the right wing, the shape of the third microporous liquid seepage structure 100c bent into the shape of the leading edge of the left flat tail is set on the left flat tail, and the fourth microporous liquid seepage structure 100d is bent into the shape of the leading edge of the right flat tail and set on the right wing. For the horizontal tail, the fifth microporous liquid-permeable structure 100e is bent into the shape of the leading edge of the vertical tail and arranged on the vertical tail.

[0038] The first distributio...

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Abstract

The invention relates to a micropore seepage structure, an airplane anti-icing system and an airplane. The microporous seepage structure includes: a first panel including a plurality of micropores; asecond panel connected with the first panel, wherein a liquid storage cavity is formed between the first panel and the second panel, and an anti-icing liquid inlet is formed in the second panel; and adamping diaphragm arranged on the inner wall of the first panel and covering the multiple micropores, wherein, when the temperature is below 0 DEG C, the damping diaphragm generates a pressure difference of a preset value on the two sides. Ice prevention is conducted through micropore leakage, the operation energy consumption of the airplane anti-icing system is low, and the aerodynamic effect ofthe airfoil profile cannot be affected.

Description

technical field [0001] The application relates to the field of aircraft anti-icing, in particular to a microporous liquid seepage structure, an aircraft anti-icing system and an aircraft. Background technique [0002] In order to prevent some parts of the aircraft from icing, or to remove the ice layer intermittently when icing, and to ensure the safe flight of the aircraft when icing, it is necessary to adopt appropriate anti-icing technology. Aircraft anti-icing technology can be divided into mechanical anti-icing and thermal anti-icing according to the working method. [0003] Thermal anti-icing: By heating the surface of the aircraft, the surface temperature of the aircraft exceeds 0°C to achieve the purpose of anti-icing or de-icing. Disadvantages of thermal anti-icing: relatively large thermal inertia, it is easy to form icicles behind the heating zone, which will disturb the air flow, low thermal efficiency and high energy consumption. [0004] Mechanical anti-icing...

Claims

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Application Information

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IPC IPC(8): B64D15/08
CPCB64D15/08
Inventor 曾锐梁肖飞杨蕊姣
Owner 中电科芜湖通用航空产业技术研究院有限公司
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