CN103727358A - Thermal insulation material structure capable of reaching low temperature - Google Patents
Thermal insulation material structure capable of reaching low temperature Download PDFInfo
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- CN103727358A CN103727358A CN201310412235.7A CN201310412235A CN103727358A CN 103727358 A CN103727358 A CN 103727358A CN 201310412235 A CN201310412235 A CN 201310412235A CN 103727358 A CN103727358 A CN 103727358A
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- thermal
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- material structure
- protective material
- low temperature
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/029—Shape or form of insulating materials, with or without coverings integral with the insulating materials layered
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
- B32B17/02—Layered products essentially comprising sheet glass, or glass, slag, or like fibres in the form of fibres or filaments
- B32B17/04—Layered products essentially comprising sheet glass, or glass, slag, or like fibres in the form of fibres or filaments bonded with or embedded in a plastic substance
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/06—Arrangements using an air layer or vacuum
- F16L59/065—Arrangements using an air layer or vacuum using vacuum
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/08—Means for preventing radiation, e.g. with metal foil
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Thermal Insulation (AREA)
Abstract
一种获得低温的隔热材料结构，其特征在于由表层，C／C或C／SiC层，Nextel／Al2O3层，复合二氧化硅气凝胶层和真空绝热板5层叠层组成；表层接触高温，高温大于2000℃，真空绝热板内侧为低温，小于25℃；该发明从结构和材料两方面同时进行设计，具有质轻、高强度、抗氧化性、抗热震性、高温稳定性、优良的耐腐蚀、耐磨损性、可重复使用等优点，整体具备多层热反射和热阻隔层，绝热性能优异，保证其内侧获得低温，可应用于航空航天等高端领域。
A thermal insulation material structure for obtaining low temperature, which is characterized in that it is composed of a surface layer, a C/C or C/SiC layer, a Nextel/Al 2 O 3 layer, a composite silica airgel layer and a vacuum insulation board 5-layer laminated layer; The surface layer is exposed to high temperature, the high temperature is greater than 2000°C, and the inner side of the vacuum insulation panel is low temperature, less than 25°C; the invention is designed from both structure and material, and has light weight, high strength, oxidation resistance, thermal shock resistance, and high temperature stability. It has the advantages of anti-corrosion, excellent corrosion resistance, wear resistance, and reusability. It has multiple layers of heat reflection and heat barrier layers as a whole, and has excellent heat insulation performance to ensure low temperature inside. It can be used in high-end fields such as aerospace.
Description
Technical field
The present invention relates to a kind of heat-insulating structure, particularly relate to a kind of thermal-protective material structure that obtains low temperature.
Background technique
When space shuttle orbiter enters earth atmosphere, because with air, fierce friction occurring, in its bottom, can produce huge heat.Because the covering of orbiter, orbital vehicle framework and it is all aluminium product substantially, the fusing point of aluminium is 660 ℃, but its intensity to not this temperature lost for a long time, so designing requirement stipulates that the temperature of orbiter, orbital vehicle exterior skin can not be over 176.7 ℃.Temperature in orbiter, orbital vehicle cabin relies on inner thermal-protective coating and air-conditioning equipment further to decline, until all suitable to space man and thermally sensitive equipment.If import the excess Temperature in cabin into, air conditioning load is overweight, can cause unnecessary energy loss, improves so the heat-insulating capability of inner thermal-protective coating, just design a kind of thermal-protective material structure that obtains low temperature, has become the task of top priority.
Application number is to disclose a kind of Cryo Heat Insulation composite nano materials multilayer heat insulation body in 200510027675.6 Chinese patent, utilize sol-gel process double coated zirconium oxide or Zirconia-alumina film on the polyester having cracked or polyamides film, using this as reflecting screen, by solvent, replace with Finishing and under normal pressure, prepare aerosil-calcium silicate composite nano materials again, using this kind of nano composite material as Spacer, utilize the method for paste in place, the 3-50 layer multi-layer heat insulator of preparing such " reflecting screen-Spacer-reflecting screen-Spacer ", and pass through Vacuum pack, reach good Cryo Heat Insulation effect, can be applicable to liquid metal vessels outer surface and the outer surface insulating with the heat insulation claimed apparatus of low temperature.
Application number is to disclose a kind of refrigerating thermal-insulation case in 201210039966.7 Chinese patent, comprise outer box frame and with the thermal-insulating body in the outer box frame of being movable to of its adaptation outside, and described thermal-insulating body is top opening type thermal-insulating body, when thermal-insulating body moves to outer box frame outside and during in opening state, cool air in thermal-insulating body can be in bottom half, can not cause a large amount of cold air to scatter and disappear, on outer box frame, also can superpose a plurality of HEATING BOX are installed simultaneously, realizing the hierarchical classification of article deposits, the layering that had both been adapted at superposeing on vertical direction of this refrigerating thermal-insulation case, can when accessing article, reduce the loss of cold air again, reduced the energy consumption of HEATING BOX.
Application number is to disclose a kind of chiller plant with novel heat insulation structure in 201210536713.0 Chinese patent, comprises at least two wallboards of splicing mutually, and wallboard consists of interior steel plate, outer steel plate, foaming layer and thermal-protective material body.Described foaming layer and thermal-protective material body are clipped between interior steel plate and outer steel plate, and thermal-protective material body is positioned at the surrounding of wallboard, and described interior steel plate and outer steel plate are all formed with flange at thermal-protective material body place.Between two adjacent wallboards, be embedded with elasticity heat insulation plaster, elasticity heat insulation plaster respectively has one at interior steel plate flange place and outer steel plate flange place, between two elasticity heat insulation plasters, is formed with cavity.Significantly reduce the inside and outside heat output of casing, guarantee the refrigeration of chiller plant.
The at present domestic thermal-protective material structural research to acquisition low temperature is less, the refrigerating structure of mentioning in above-mentioned patent is all only applied in the liquid metal vessels such as refrigerator, boats and ships, storage tank, and its cold and heat insulation structure has been ignored the application of high performance material, single designs from configuration aspects, and the thermal insulating material of its low side and narrow applicable situation have limited its application in Aero-Space insulation high-end field.Therefore, from material and structure two aspects, set about, exploring a kind of thermal-protective material structure applications that obtains low temperature is a study hotspot now in the heat insulation field of Aero-Space simultaneously.
Summary of the invention
The present invention is intended to overcome the deficiency of existing heat-insulating structure research, and a kind of thermal-protective material structure that obtains low temperature is provided.The thermal-protective material structure that this kind obtains low temperature combines high performance material with rational structural design, have excellent insulation ability, is mainly used in the heat insulation field of Aero-Space.
For the problems referred to above, the invention provides a kind of thermal-protective material structure that obtains low temperature, it is characterized in that by top layer C/C or C/SiC layer, Nextel/Al
2o
3layer, composite silicon dioxide aerogel layer and vacuum heat-insulating plate 5 layer laminate form.
Described top layer is high temp, infrared radiation coating, waterproof, anticorrosion, and can improve hyperthermia radiation performance.
Described C/C is high-density carbon/carbon/charcoal composite heat-insulated material, and density is 1.8-2.3g/cm
3serviceability temperature is 1000-3000 ℃, carbon/carbon composite forms a kind of charcoal fiber net structure, and the charcoal/carbonaceous of zone of dispersion is bonded together at the infall of fiber, and wherein the fiber of 70-90% forms the hole being interconnected, the matrix of high porosity and fiber orientation make perpendicular to the thermal conductivity in layer of fibers direction low, the heat-shielding performance of existing excellence, has again excellent comprehensive mechanical property, structure-function integration, good stability, long service life.
Described C/SiC is that 2.5D weaving carbon fiber strengthens carbon/silicon carbide ceramic matrix composite, and 2.5D braiding C/SiC composite material at high temperature has lower coefficient of linear thermal expansion, good with matrix connectivity; Simultaneously C/SiC composite material has high strength, high temperature resistant, low density, high fracture property, resist chemical, thermal shock resistance and the incomparable oxidation resistance of C/C composite material, the anti-ablated surface heat-insulating tile made from C/SiC composite material, produces the high effective solar heat protection system that formed when hot in aerospace craft atmospheric reentry and air friction.
Described Nextel/Al
2o
3for Nextel oxide fibre REINFORCED Al
2o
3ceramic matric composite, Nextel oxide fibre content is 10-30%, Nextel oxide fibre has compared with high tensile strength, preeminent high temperature resistance, corrosion resistance, low distortion, thermal conductivity is little, thermal shock resistance is strong, voids is low and unique series of advantages such as electrical properties, the Al strengthening with Nextel oxide fibre
2o
3ceramic matric composite heat-shielding performance is good, can bear jerk and high low temperature alternation, good thermal stability.
Described composite silicon dioxide aerogel layer strengthens SiO by glass fibre
2aerogel forms, and thermal conductivity is 8-15mW/mK.One side SiO
2aerogel has nanoporous network structure, its nanometer aperture can significantly reduce the hot conduction and convection of gas molecule and conduct heat, very thin nanometer skeleton particle can significantly reduce solid state heat conduction, there is extremely low thermal conductivity, also be the lightest so far solid, be a kind of comparatively desirable efficient and light weight thermal-protective material simultaneously; On the other hand, can crack the adding of glass fibre the toughening mechanisms such as deflection, fibre debonding, fiber are extracted, fiber-bridged, increase the energy absorbing before composite failure, thereby improve the mechanical property of material, and glass fibre itself has too and blocks preferably infrared radiation effect and heat-shielding performance.
Described heat conductivity of vacuum insulation panel is 1-5mW/mK, vacuum heat-insulating plate is to blow out the byssaceous microglass fiber of diameter 3.5-5.5 μ m by cullet melting and by centrifuge method, between fiber and fiber, crossings on different level is wound around, micro-pore and the hole with a large amount of inside and outside UNICOMs, by curing blooming processing, forming, is splendid adiabatic new material.
Described top layer contact high temperature, high temperature is greater than 2000 ℃, and vacuum heat-insulating plate inner side is low temperature, is less than 25 ℃.
Major advantage of the present invention is: 1. this thermal-protective material structure light weight, to compare with traditional material, and total thickness can reduce by 50%; 2. through Multi-layer thermal reflection and heat rejection, whole heat-insulating property is excellent, guarantees that its inner side obtains low temperature; 3. there is high strength, oxidative stability, thermal shock resistance; 4. there is high-temperature stability, good corrosion-resistant, abrasion resistance properties; 5. reusable.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention, and wherein 10 is top layer, and 20 is C/C or C/SiC layer, and 30 is Nextel/Al
2o
3layer, 40 is composite silicon dioxide aerogel layer, 50 is vacuum heat-insulating plate.
Embodiment
Below in conjunction with specific embodiment, further illustrate the present invention, should understand these embodiments is only not used in and limits the scope of the invention for the present invention is described, after having read the present invention, those skilled in the art all fall within the application's claims to the modification of the various equivalent form of values of the present invention and limit.
Embodiment 1
A thermal-protective material structure that obtains low temperature, comprises top layer, C/C layer, Nextel/Al
2o
3layer, composite silicon dioxide aerogel layer and vacuum heat-insulating plate 5 layer laminate form, and top layer is high temp, infrared radiation coating; C/C layer is that density is 1.8g/cm
3charcoal/charcoal composite heat-insulated material; Nextel/Al
2o
3layer is the Al being strengthened by 10% Nextel oxide fibre
2o
3ceramic matric composite; Composite silicon dioxide aerogel layer is the SiO that glass fibre strengthens
2aerogel, this layer of thermal conductivity is 8mW/mK; Heat conductivity of vacuum insulation panel is 3mW/mK; This structure top layer contact high temperature, high temperature is greater than 2000 ℃, and vacuum heat-insulating plate inner side is low temperature, is less than 25 ℃.
Embodiment 2
A thermal-protective material structure that obtains low temperature, comprises top layer, C/SiC layer, Nextel/Al
2o
3layer, composite silicon dioxide aerogel layer and vacuum heat-insulating plate 5 layer laminate form, and top layer is high temp, infrared radiation coating; C/SiC layer is that 2.5D weaving carbon fiber strengthens carbon/silicon carbide ceramic matrix composite; Nextel/Al
2o
3layer is the Al being strengthened by 24% Nextel oxide fibre
2o
3ceramic matric composite; Composite silicon dioxide aerogel layer is the SiO that glass fibre strengthens
2aerogel, this layer of thermal conductivity is that 12mW/mK heat conductivity of vacuum insulation panel is 5mW/mK; This structure top layer contact high temperature, high temperature is greater than 2000 ℃, and vacuum heat-insulating plate inner side is low temperature, is less than 25 ℃.
Above are only two embodiments of the present invention, but design concept of the present invention is not limited to this, allly utilizes this design to carry out the change of unsubstantiality to the present invention, all should belong to the behavior of invading the scope of protection of the invention.In every case be the content that does not depart from technical solution of the present invention, any type of simple modification, equivalent variations and the remodeling above embodiment done according to technical spirit of the present invention, still belong to the protection domain of technical solution of the present invention.
Claims (8)
1. a thermal-protective material structure that obtains low temperature, is characterized in that by top layer, C/C or C/SiC layer, Nextel/Al
2o
3layer, composite silicon dioxide aerogel layer and vacuum heat-insulating plate 5 layer laminate form.
2. thermal-protective material structure according to claim 1, is characterized in that described top layer is high temp, infrared radiation coating.
3. thermal-protective material structure according to claim 1, is characterized in that described C/C is high-density carbon/carbon/charcoal composite heat-insulated material, and density is 1.8-2.3g/cm
3, serviceability temperature is 1000-3000 ℃.
4. thermal-protective material structure according to claim 1, is characterized in that described C/SiC is that 2.5D weaving carbon fiber strengthens carbon/silicon carbide ceramic matrix composite.
5. thermal-protective material structure according to claim 1, is characterized in that described Nextel/Al
2o
3for Nextel oxide fibre REINFORCED Al
2o
3ceramic matric composite, Nextel oxide fibre content is 10-30%.
6. thermal-protective material structure according to claim 1, is characterized in that described composite silicon dioxide aerogel layer strengthens SiO by glass fibre
2aerogel forms, and thermal conductivity is 8-15mW/mK.
7. thermal-protective material structure according to claim 1, is characterized in that described heat conductivity of vacuum insulation panel is 1-5mW/mK.
8. thermal-protective material structure according to claim 1, is characterized in that described top layer contact high temperature, and high temperature is greater than 2000 ℃, and vacuum heat-insulating plate inner side is low temperature, is less than 25 ℃.
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| CN201310412235.7A CN103727358B (en) | 2013-09-11 | 2013-09-11 | A kind of thermal-protective material structure obtaining low temperature |
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| CN201310412235.7A CN103727358B (en) | 2013-09-11 | 2013-09-11 | A kind of thermal-protective material structure obtaining low temperature |
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| CN103727358B CN103727358B (en) | 2015-10-21 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103979993A (en) * | 2014-05-27 | 2014-08-13 | 西安超码科技有限公司 | Preparation method of large-sized carbon/silicon carbide composite heat-insulting baseplates |
| CN105109709A (en) * | 2015-08-25 | 2015-12-02 | 中国人民解放军国防科学技术大学 | Thermal insulation/protection integrated space debris protection structure and application thereof |
| CN106439392A (en) * | 2016-09-08 | 2017-02-22 | 南京航空航天大学 | High-temperature-resistant anti-oxidation lightweight thermal insulation material |
| CN112776427A (en) * | 2019-11-11 | 2021-05-11 | 湖南众德新材料科技有限公司 | Carbon-carbon composite material battery protection board |
| CN113978046A (en) * | 2021-11-09 | 2022-01-28 | 厦门大学 | Thermal protection structure and preparation method thereof |
| CN114248524A (en) * | 2021-11-13 | 2022-03-29 | 韩元良 | Vapor-barrier waterproof layer, cold insulation material, and preparation method and application thereof |
| CN115304814A (en) * | 2022-09-05 | 2022-11-08 | 上海宇航系统工程研究所 | Light composite material heat insulation tile for aerospace and manufacturing method thereof |
| CN117754931A (en) * | 2023-12-22 | 2024-03-26 | 上海康碳复合材料科技有限公司 | A multi-layer structure high-efficiency thermal insulation felt and its preparation method and application |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103979993A (en) * | 2014-05-27 | 2014-08-13 | 西安超码科技有限公司 | Preparation method of large-sized carbon/silicon carbide composite heat-insulting baseplates |
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| CN112776427A (en) * | 2019-11-11 | 2021-05-11 | 湖南众德新材料科技有限公司 | Carbon-carbon composite material battery protection board |
| CN113978046A (en) * | 2021-11-09 | 2022-01-28 | 厦门大学 | Thermal protection structure and preparation method thereof |
| CN114248524A (en) * | 2021-11-13 | 2022-03-29 | 韩元良 | Vapor-barrier waterproof layer, cold insulation material, and preparation method and application thereof |
| CN115304814A (en) * | 2022-09-05 | 2022-11-08 | 上海宇航系统工程研究所 | Light composite material heat insulation tile for aerospace and manufacturing method thereof |
| CN117754931A (en) * | 2023-12-22 | 2024-03-26 | 上海康碳复合材料科技有限公司 | A multi-layer structure high-efficiency thermal insulation felt and its preparation method and application |
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| CN103727358B (en) | 2015-10-21 |
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