CN102914111A - Aircraft surface skin cooling device - Google Patents
Aircraft surface skin cooling device Download PDFInfo
- Publication number
- CN102914111A CN102914111A CN2012104092817A CN201210409281A CN102914111A CN 102914111 A CN102914111 A CN 102914111A CN 2012104092817 A CN2012104092817 A CN 2012104092817A CN 201210409281 A CN201210409281 A CN 201210409281A CN 102914111 A CN102914111 A CN 102914111A
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- cooler
- discharge orifice
- cold
- storage tank
- dry ice
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Abstract
The invention relates to an aircraft surface skin cooling device which comprises a dry-ice cold storage tank (1), a cold dissipater (2) and a rubber heat-proof pad (3). A bottom opening of the dry-ice cold storage tank (1) is connected with the upper portion of the cold dissipater (2). A cold dissipation plate (6) is disposed in a hole on the upper portion of the cold dissipater (2), connected with the bottom opening of the dry-ice cold storage tank (1). Three to five retarding net layers (9) are transversely disposed in inner space of the cold dissipater (2) below the cold dissipation plate (6). A lower opening of the cold dissipater (2) is connected with the rubber heat-proof pad (3), and connection edges are sealed. Compared with the prior art, the aircraft surface skin cooling device is capable of evenly and effectively lowering temperature of local surface of aircraft parts without damage.
Description
Technical field
The present invention is a kind of aircraft surfaces covering heat sink, belongs to the technical field of structures of product.This device is that a kind of the maintenance when detecting aircraft lowered the temperature to its surface.
Background technology
In recent years, infrared and optical interference detection method is applied to during maintenance, outfield at the labour aircraft detect gradually as the new technology of Non-Destructive Testing.Fuselage, wing and other aircraft components be the normal various covering sandwich materials (such as thin skin honeycomb bonded structure, foam bonded structure etc.) that use in the manufacturing, for they are detected, to determine after aircraft flight several years, whether the problems such as unsticking, layering, ponding have appearred, the micro-displacement that need to monitor skin-surface when skin-surface causes variations in temperature changes, according to the different temperatures difference that surperficial micro-displacement changes of getting off the plane, find the defective (unsticking, layering, ponding) in the covering sandwich adhesives.Generally in laboratory and normal temperature environment, need to heat to detected surface; And after aircraft was exposed to the sun in the sun, the skin-surface temperature was much higher than normal temperature, just need to do cooling and process.
Summary of the invention
The present invention designs for the needs of above-mentioned infrared and optical interference detection technique just a kind of aircraft surfaces covering heat sink is provided, this installs with dry ice as low-temperature receiver, directly connect cooler and form low speed, the uniform Cryogenic air of plateau temperature, reach the purpose to the aircraft surfaces cooling refrigeration.
The objective of the invention is to realize by following technical measures:
This kind aircraft surfaces covering heat sink is characterized in that:
This device is comprised of dry ice cold storage tank (1), cooler (2) and rubber heat insulating (3), the bottom of dry ice cold storage tank (1) has opening to be connected with the top of cooler (2), connect edge seal, top cover (4) is arranged at the top of dry ice cold storage tank (1), with the dry ice of conveniently packing into, bottom opening is by valve (5) control folding; Valve (5) is comprised of two metallic plates with slotted hole up and down, by the changing of the relative positions adjustable opening amount of metallic plate.A few row's jubes are arranged on the metallic plate of top, and when temp-lowering guard setting work, jube can stop a part of dry ice;
In the top of cooler (2) and the hole that the bottom opening of dry ice cold storage tank (1) is connected a cold radiation plate (6) is set, the upper end of cold radiation plate (6) is no more than the upper surface of cooler (2), be processed with overflow discharge orifice (7) in a row downwards from the upper surface of cold radiation plate (6), the degree of depth of overflow discharge orifice (7) is not less than half of cold radiation plate (6) thickness, the diameter of overflow discharge orifice (7) is 30～40mm, distance between the adjacent overflow discharge orifice (7) is 10～20mm, upwards be processed with underflow discharge orifice (8) in a row from the lower surface of cooler (2), the degree of depth of underflow discharge orifice (8) is not less than half of cold radiation plate (6) thickness, the diameter of underflow discharge orifice (8) is 5～10mm, and the distance between the adjacent underflow discharge orifice (8) is 3～5mm;
In the inner space of the cooler (2) of cold radiation plate (6) below, 3～5 layers of choked flow net of horizontally set (9), the lower openings of cooler (2) is connected with rubber heat insulating (3), connects edge seal.
Described choked flow net (9) adopts metal material to make, and sizing grid is equivalent to the aperture of Ф 0.5～2.5mm, and the sizing grid of choked flow net (9) from top to bottom layer successively decreases.
Apparatus of the present invention are directly freezed by dry ice take dry ice as low-temperature receiver, make air cooling-down.Dry ice is positioned in the cold storage tank.Cold storage tank forms low speed, the uniform Cryogenic air of plateau temperature by cooler, and aircraft surfaces is lowered the temperature.Use soft rubber heat insulating around the cold delivery outlet of cold emanator, reduce Cryogenic air and flow to nonclient area, allow simultaneously the working region to have certain curved surface to change.
Description of drawings
Fig. 1 is the structural representation of apparatus of the present invention
Fig. 2 is the structure cross-sectional schematic of apparatus of the present invention
The specific embodiment
Below with reference to drawings and Examples technical solution of the present invention is further described:
Shown in accompanying drawing 1～2, this kind aircraft surfaces covering heat sink is characterized in that:
This device is comprised of dry ice cold storage tank 1, cooler 2 and rubber heat insulating 3, the bottom of dry ice cold storage tank 1 has opening to be connected with the top of cooler 2, connect edge seal, top cover 4 dry ice of conveniently packing into is arranged at the top of dry ice cold storage tank 1, and bottom opening is by valve 5 control foldings; Valve 5 is comprised of two metallic plates with slotted hole up and down, by the changing of the relative positions adjustable opening amount of metallic plate.A few row's jubes are arranged on the metallic plate of top, and when temp-lowering guard setting work, jube can stop a part of dry ice, and valve 5 is comprised of two metallic plates with slotted hole up and down, by the changing of the relative positions adjustable opening amount of metallic plate.A few row's jubes are arranged on the metallic plate of top, and when temp-lowering guard setting work, jube can stop a part of dry ice;
In the top of cooler 2 and the hole that the bottom opening of dry ice cold storage tank 1 is connected a cold radiation plate 6 is set, the upper end of cold radiation plate 6 is no more than the upper surface of cooler 2, be processed with overflow discharge orifice 7 in a row downwards from the upper surface of cold radiation plate 6, the degree of depth of overflow discharge orifice 7 is not less than half of cold radiation plate 6 thickness, the diameter of overflow discharge orifice 7 is 30～40mm, distance between the adjacent overflow discharge orifice 7 is 10～20mm, upwards be processed with underflow discharge orifice 8 in a row from the lower surface of cooler 2, the degree of depth of underflow discharge orifice 8 is not less than half of cold radiation plate 6 thickness, the diameter of underflow discharge orifice 8 is 5～10mm, and the distance between the adjacent underflow discharge orifice 8 is 3～5mm;
In the inner space of the cooler 2 of cold radiation plate 6 belows, 3～5 layers of choked flow net 9 of horizontally set, the lower openings of cooler 2 is connected with rubber heat insulating 3, connects the edge and adopts sealing strip 4 sealings.
Described choked flow net 9 adopts metal material to make, and sizing grid is equivalent to the aperture of Ф 0.5～2.5mm, and the sizing grid of choked flow net 9 from top to bottom layer successively decreases.Around the outer wall of cooler 2 sheet rubber is housed, makes interval air between cooler 2 working faces and the quilt cooling surface.
Should first optical instrument be transferred to duty during use with the micro-displacement variation of monitoring skin-surface, again apparatus of the present invention are positioned over tested zone and carry out preliminary examination, adjust detection system according to the preliminary examination effect, guarantee the high efficiency and the correctness that detect.
Compared with prior art, apparatus of the present invention can evenly reduce the temperature of aircraft components local surfaces effectively under undamaged prerequisite.
Claims (2)
1. aircraft surfaces covering heat sink, it is characterized in that: this device is comprised of dry ice cold storage tank (1), cooler (2) and rubber heat insulating (3), the bottom of dry ice cold storage tank (1) has opening to be connected with the top of cooler (2), connect edge seal, top cover (4) dry ice of conveniently packing into is arranged at the top of dry ice cold storage tank (1), and bottom opening is by valve (5) control folding;
In the top of cooler (2) and the hole that the bottom opening of dry ice cold storage tank (1) is connected a cold radiation plate (6) is set, the upper end of cold radiation plate (6) is no more than the upper surface of cooler (2), be processed with overflow discharge orifice (7) in a row downwards from the upper surface of cold radiation plate (6), the degree of depth of overflow discharge orifice (7) is not less than half of cold radiation plate (6) thickness, the diameter of overflow discharge orifice (7) is 30～40mm, distance between the adjacent overflow discharge orifice (7) is 10～20mm, upwards be processed with underflow discharge orifice (8) in a row from the lower surface of cooler (2), the degree of depth of underflow discharge orifice (8) is not less than half of cold radiation plate (6) thickness, the diameter of underflow discharge orifice (8) is 5～10mm, and the distance between the adjacent underflow discharge orifice (8) is 3～5mm;
In the inner space of the cooler (2) of cold radiation plate (6) below, 3～5 layers of choked flow net of horizontally set (9), the lower openings of cooler (2) is connected with rubber heat insulating (3), connects edge seal.
2. aircraft surfaces covering heat sink according to claim 1, it is characterized in that: described choked flow net (9) adopts metal material to make, sizing grid is equivalent to the aperture of Ф 0.5～2.5mm, and the sizing grid of choked flow net (9) from top to bottom layer successively decreases.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210409281.7A CN102914111B (en) | 2012-10-24 | 2012-10-24 | Aircraft surface skin cooling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210409281.7A CN102914111B (en) | 2012-10-24 | 2012-10-24 | Aircraft surface skin cooling device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102914111A true CN102914111A (en) | 2013-02-06 |
| CN102914111B CN102914111B (en) | 2014-11-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210409281.7A Active CN102914111B (en) | 2012-10-24 | 2012-10-24 | Aircraft surface skin cooling device |
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| Country | Link |
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| CN (1) | CN102914111B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100273A (en) * | 2017-11-29 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft fuel oil cooling system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN2572261Y (en) * | 2002-10-10 | 2003-09-10 | 沈阳航达机载设备公司 | Ground air condition vehicle for airplane |
| CN2828623Y (en) * | 2005-11-29 | 2006-10-18 | 广东省吉荣空调设备公司 | Air conditioner set for aircraft on loading bridge |
| CN101190713A (en) * | 2006-11-20 | 2008-06-04 | 董鹏生 | Airplane floor synthetic guarantee trolley |
| CN201245244Y (en) * | 2008-07-30 | 2009-05-27 | 周立 | Mobile ice-reserving air conditioning equipment for airplane waiting for guests |
| WO2009146843A1 (en) * | 2008-06-03 | 2009-12-10 | Airbus Operations Gmbh | System and method for cooling a device subjected to heat in a vehicle, particularly an aircraft |
| US20110186263A1 (en) * | 2008-07-31 | 2011-08-04 | Airbus Operations Gmbh | Heat exchanger for the outer skin of an aircraft |
| CN102295072A (en) * | 2011-05-04 | 2011-12-28 | 中国航空工业集团公司西安飞机设计研究所 | Single-layer air-liquid aircraft skin heat exchange method |
-
2012
- 2012-10-24 CN CN201210409281.7A patent/CN102914111B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2572261Y (en) * | 2002-10-10 | 2003-09-10 | 沈阳航达机载设备公司 | Ground air condition vehicle for airplane |
| CN2828623Y (en) * | 2005-11-29 | 2006-10-18 | 广东省吉荣空调设备公司 | Air conditioner set for aircraft on loading bridge |
| CN101190713A (en) * | 2006-11-20 | 2008-06-04 | 董鹏生 | Airplane floor synthetic guarantee trolley |
| WO2009146843A1 (en) * | 2008-06-03 | 2009-12-10 | Airbus Operations Gmbh | System and method for cooling a device subjected to heat in a vehicle, particularly an aircraft |
| CN201245244Y (en) * | 2008-07-30 | 2009-05-27 | 周立 | Mobile ice-reserving air conditioning equipment for airplane waiting for guests |
| US20110186263A1 (en) * | 2008-07-31 | 2011-08-04 | Airbus Operations Gmbh | Heat exchanger for the outer skin of an aircraft |
| CN102295072A (en) * | 2011-05-04 | 2011-12-28 | 中国航空工业集团公司西安飞机设计研究所 | Single-layer air-liquid aircraft skin heat exchange method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100273A (en) * | 2017-11-29 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft fuel oil cooling system |
| CN108100273B (en) * | 2017-11-29 | 2021-08-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel cooling system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102914111B (en) | 2014-11-26 |
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