CN103727358B - A kind of thermal-protective material structure obtaining low temperature - Google Patents
A kind of thermal-protective material structure obtaining low temperature Download PDFInfo
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- CN103727358B CN103727358B CN201310412235.7A CN201310412235A CN103727358B CN 103727358 B CN103727358 B CN 103727358B CN 201310412235 A CN201310412235 A CN 201310412235A CN 103727358 B CN103727358 B CN 103727358B
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- 239000000463 material Substances 0.000 title claims abstract description 29
- 239000002131 composite material Substances 0.000 claims abstract description 26
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 20
- 239000004964 aerogel Substances 0.000 claims abstract description 15
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 claims abstract description 11
- 239000000377 silicon dioxide Substances 0.000 claims abstract description 10
- 235000012239 silicon dioxide Nutrition 0.000 claims abstract description 10
- 239000000203 mixture Substances 0.000 claims abstract description 5
- 238000009413 insulation Methods 0.000 claims description 18
- 239000000835 fiber Substances 0.000 claims description 15
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 10
- 229910052799 carbon Inorganic materials 0.000 claims description 10
- 239000003365 glass fiber Substances 0.000 claims description 6
- 239000000919 ceramic Substances 0.000 claims description 5
- 239000003610 charcoal Substances 0.000 claims description 5
- HPNSNYBUADCFDR-UHFFFAOYSA-N chromafenozide Chemical compound CC1=CC(C)=CC(C(=O)N(NC(=O)C=2C(=C3CCCOC3=CC=2)C)C(C)(C)C)=C1 HPNSNYBUADCFDR-UHFFFAOYSA-N 0.000 claims description 5
- 230000005855 radiation Effects 0.000 claims description 5
- 239000011248 coating agent Substances 0.000 claims description 4
- 238000000576 coating method Methods 0.000 claims description 4
- 230000002787 reinforcement Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000011153 ceramic matrix composite Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 3
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 3
- 238000009941 weaving Methods 0.000 claims description 3
- 229910004298 SiO 2 Inorganic materials 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 6
- 230000035939 shock Effects 0.000 abstract description 4
- 230000007797 corrosion Effects 0.000 abstract description 3
- 238000005260 corrosion Methods 0.000 abstract description 3
- 230000001590 oxidative effect Effects 0.000 abstract description 2
- 230000004888 barrier function Effects 0.000 abstract 1
- 229910000831 Steel Inorganic materials 0.000 description 8
- 239000010959 steel Substances 0.000 description 8
- 238000000034 method Methods 0.000 description 4
- 238000004378 air conditioning Methods 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000005187 foaming Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000012761 high-performance material Substances 0.000 description 2
- 229910001338 liquidmetal Inorganic materials 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000002086 nanomaterial Substances 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000005439 thermosphere Substances 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 206010020843 Hyperthermia Diseases 0.000 description 1
- 239000004952 Polyamide Substances 0.000 description 1
- 101710198474 Spike protein Proteins 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 239000000378 calcium silicate Substances 0.000 description 1
- 229910052918 calcium silicate Inorganic materials 0.000 description 1
- 230000036461 convulsion Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 239000006063 cullet Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000036031 hyperthermia Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000012212 insulator Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002114 nanocomposite Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 229920002647 polyamide Polymers 0.000 description 1
- 229920000728 polyester Polymers 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 230000000191 radiation effect Effects 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 238000003980 solgel method Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910001928 zirconium oxide Inorganic materials 0.000 description 1
Classifications
-
- 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
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Thermal Insulation (AREA)
Abstract
Obtain a thermal-protective material structure for 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 composition; Top layer contact high temperature, high temperature is greater than 2000 DEG C, is low temperature, is less than 25 DEG C inside vacuum heat-insulating plate; This invention designs from structure and material two aspect simultaneously, there is light weight, high strength, oxidative stability, thermal shock resistance, high-temperature stability, excellent corrosion-resistant, wearability, the advantage such as reusable, entirety possesses Multi-layer thermal reflection and thermal barrier layer, heat-insulating property is excellent, ensure to obtain low temperature inside it, can be applicable to the high-end fields such as Aero-Space.
Description
Technical field
The present invention relates to a kind of heat-insulating structure, particularly relate to a kind of thermal-protective material structure obtaining low temperature.
Background technique
When space shuttle orbiter enters earth atmosphere, because occurring fiercely to rub with air, huge heat can be produced in its bottom.Because orbiter, orbital vehicle framework and its covering are all aluminium product substantially, the fusing point of aluminium is 660 DEG C, but its intensity loses for a long time to not this temperature, and therefore designing requirement specifies that the temperature of orbiter, orbital vehicle exterior skin can not more than 176.7 DEG C.Temperature in orbiter, orbital vehicle cabin relies on internal partition thermosphere and air-conditioning equipment will decline further, until be all suitable for space man and thermally sensitive equipment.If the temperature imported in cabin is too high, air conditioning load is overweight, can cause unnecessary energy loss, so improves the heat-insulating capability of internal partition thermosphere, designs a kind of thermal-protective material structure obtaining low temperature and just become the task of top priority.
Application number is disclose a kind of Cryo Heat Insulation composite nano materials multilayer thermal insulation in the Chinese patent of 200510027675.6, utilize sol-gel process double coated zirconium oxide or Zirconia-alumina film on the polyester cracked or polyamides film, in this, as reflecting screen, under normal pressure, aerosil-calcium silicate composite nano materials is prepared again by solvent replacement and Finishing, using this kind of nano composite material as Spacer, utilize the method for paste in place, prepare the 3-50 layer multi-layer heat insulator of 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 low temperature insulation requirement device.
Application number is disclose a kind of refrigerating thermal-insulation case in the Chinese patent of 201210039966.7, comprise outer-layer box body framework and the thermal-insulating body be movable to outside outer-layer box body framework with its adaptation, and described thermal-insulating body is top opening type thermal-insulating body, when thermal-insulating body to move to outside outer-layer box body framework and is in opening state, cool air in thermal-insulating body can be in bottom half, a large amount of cold air can not be caused to scatter and disappear, outer-layer box body framework also can superpose simultaneously and multiple HEATING BOX is installed, the hierarchical classification realizing article is deposited, this refrigerating thermal-insulation case had both been adapted at vertical direction carries out superposition layering, the loss of cold air can be reduced again when accessing article, reduce the energy consumption of HEATING BOX.
Application number is disclose a kind of chiller plant with novel heat preservation structure in the Chinese patent of 201210536713.0, comprises at least two pieces of wallboards spliced mutually, and wallboard is made up 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.Be embedded with Elastic heat insulation bar between two pieces of adjacent wallboards, Elastic heat insulation bar respectively has one at interior steel plate flange place and outer steel plate flange place, is formed with cavity between two Elastic heat insulation bars.Significantly reduce the heat output inside and outside casing, ensure the refrigeration of chiller plant.
The domestic thermal-protective material structural research to obtaining low temperature is less at present, the refrigerating structure mentioned 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 have 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 limit its application in Aero-Space insulation high-end field.Therefore, set about from materials and structures two aspect, exploring a kind of thermal-protective material structure obtaining low temperature, to be applied to the heat insulation field of Aero-Space be a study hotspot now simultaneously.
Summary of the invention
The present invention is intended to the deficiency overcoming the research of existing heat-insulating structure, provides a kind of thermal-protective material structure obtaining low temperature.High performance material combines with rational structural design by the thermal-protective material structure that this kind obtains low temperature, has 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 obtaining 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 composition.
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 DEG C, carbon/carbon composite forms a kind of Carbon fibe web frame, 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 be interconnected, the matrix of high porosity and fiber-wall-element model make perpendicular to the thermal conductivity on 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 weaves C/SiC composite material and at high temperature has lower coefficient of linear thermal expansion, good with matrix connectivity; Simultaneously C/SiC composite material has high strength, the oxidation resistance that high temperature resistant, low density, high fracture property, resist chemical, thermal shock resistance and C/C composite material are incomparable, the anti-yaw damper surface heat-insulating tile made with C/SiC composite material, constitutes effective solar heat protection system when aerospace craft atmospheric reentry and air friction produce high heat.
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 the series of advantages such as high tensile strength, preeminent high temperature resistance, corrosion resistance, low distortion, thermal conductivity is little, thermal shock resistance is strong, the low electrical properties with uniqueness of voids, the Al strengthened 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 is by glass fiber reinforcement SiO
2aerogel forms, and thermal conductivity is 8-15mW/mK.SiO on the one hand
2aerogel has nanoporous network structure, its nanometer aperture can significantly reduce gas molecule heat transfer and heat transfer by convection, very thin nanometer skeleton particle significantly can reduce solid state heat conduction, there is extremely low thermal conductivity, also be solid the lightest so far, be a kind of ideal efficient and light weight thermal-protective material simultaneously; On the other hand, glass fibre add toughening mechanisms such as can cracking deflection, fibre debonding, spike protein gene, fiber-bridged, the energy absorbed before increasing composite failure, thus improve the mechanical property of material, and glass fibre itself has too and blocks infrared radiation effect and heat-shielding performance preferably.
Described heat conductivity of vacuum insulation panel is 1-5mW/mK, vacuum heat-insulating plate is by cullet melting and blows out diameter 3.5-5.5 μm of byssaceous microglass fiber by centrifuge method, between fiber and fiber, crossings on different level is wound around, there is micro-pore and the hole of a large amount of inside and outside UNICOMs, being formed by the process of solidification blooming, is splendid adiabatic new material.
Described top layer contact high temperature, high temperature is greater than 2000 DEG C, is low temperature, is less than 25 DEG C inside vacuum heat-insulating plate.
Major advantage of the present invention is: 1. this thermal-protective material structure light weight, and compared with traditional material, total thickness can reduce by 50%; 2. through Multi-layer thermal reflection and heat rejection, overall heat-insulating property is excellent, ensures to obtain low temperature inside it; 3. there is high strength, oxidative stability, thermal shock resistance; 4. there is high-temperature stability, excellent 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, and 50 is vacuum heat-insulating plate.
Embodiment
Below in conjunction with specific embodiment, illustrate the present invention further, these embodiments should be understood only be not used in for illustration of the present invention and limit the scope of the invention, after having read the present invention, the amendment of those skilled in the art to the various equivalent form of value of the present invention has all fallen within the application's claims and limited.
Embodiment 1
Obtain a thermal-protective material structure for low temperature, comprise top layer, C/C layer, Nextel/Al
2o
3layer, composite silicon dioxide aerogel layer and vacuum heat-insulating plate 5 layer laminate composition, top layer is high temp, infrared radiation coating; C/C layer is density is 1.8g/cm
3charcoal/charcoal composite heat-insulated material; Nextel/Al
2o
3layer is the Al strengthened by the Nextel oxide fibre of 10%
2o
3ceramic matric composite; Composite silicon dioxide aerogel layer is the SiO of glass fiber reinforcement
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 DEG C, is low temperature, is less than 25 DEG C inside vacuum heat-insulating plate.
Embodiment 2
Obtain a thermal-protective material structure for low temperature, comprise top layer, C/SiC layer, Nextel/Al
2o
3layer, composite silicon dioxide aerogel layer and vacuum heat-insulating plate 5 layer laminate composition, 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 strengthened by the Nextel oxide fibre of 24%
2o
3ceramic matric composite; Composite silicon dioxide aerogel layer is the SiO of glass fiber reinforcement
2aerogel, this layer of thermal conductivity is 12mW/mK heat conductivity of vacuum insulation panel is 5mW/mK; This structure top layer contact high temperature, high temperature is greater than 2000 DEG C, is low temperature, is less than 25 DEG C inside vacuum heat-insulating plate.
Above are only two embodiments of the present invention, but design concept of the present invention is not limited thereto, all changes utilizing this design the present invention to be carried out to unsubstantiality, all should belong to the behavior of invading the scope of protection of the invention.In every case be the content not departing from technical solution of the present invention, any type of simple modification, equivalent variations and the remodeling done above embodiment according to technical spirit of the present invention, still belong to the protection domain of technical solution of the present invention.
Claims (2)
1. obtain a thermal-protective material structure for 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 composition, its mesexine is high temp, infrared radiation coating, and C/C is high-density carbon/carbon/charcoal composite heat-insulated material, and density is 1.8-2.3g/cm
3, C/SiC is that 2.5D weaving carbon fiber strengthens carbon/silicon carbide ceramic matrix composite, Nextel/Al
2o
3for Nextel oxide fibre REINFORCED Al
2o
3ceramic matric composite, Nextel oxide fibre content is 10-30%, and composite silicon dioxide aerogel layer is by glass fiber reinforcement SiO
2aerogel forms, and thermal conductivity is 8-15mW/mK, and heat conductivity of vacuum insulation panel is 1-5mW/mK.
2. thermal-protective material structure according to claim 1, it is characterized in that described top layer contact high temperature, high temperature is greater than 2000 DEG C, is low temperature, is less than 25 DEG C inside vacuum heat-insulating plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310412235.7A CN103727358B (en) | 2013-09-11 | 2013-09-11 | A kind of thermal-protective material structure obtaining low temperature |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310412235.7A CN103727358B (en) | 2013-09-11 | 2013-09-11 | A kind of thermal-protective material structure obtaining low temperature |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103727358A CN103727358A (en) | 2014-04-16 |
| CN103727358B true CN103727358B (en) | 2015-10-21 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103979993B (en) * | 2014-05-27 | 2015-07-29 | 西安超码科技有限公司 | A kind of preparation method of large size carbon/carbon/silicon carbide composite material heat insulation bottom board |
| CN105109709B (en) * | 2015-08-25 | 2017-12-22 | 中国人民解放军国防科学技术大学 | One kind prevents heat-insulated/protection integrated space debris prevention structure and its application |
| CN106439392B (en) * | 2016-09-08 | 2018-09-25 | 南京航空航天大学 | A kind of light heat-insulating material of fire-resistant oxidation resistant |
| 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 |
| CN113978046B (en) * | 2021-11-09 | 2022-07-29 | 厦门大学 | A kind of thermal protection structure and preparation method thereof |
| CN114248524B (en) * | 2021-11-13 | 2024-07-19 | 铂市(上海)智能科技有限公司 | Steam-isolating waterproof layer, cold-insulating material, 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 |
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| CN201866468U (en) * | 2010-11-11 | 2011-06-15 | 太仓宏大方圆电气有限公司 | Wet superfine glass wool vacuum insulation panel |
-
2013
- 2013-09-11 CN CN201310412235.7A patent/CN103727358B/en active Active
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|---|---|---|---|---|
| WO1999036725A1 (en) * | 1998-01-15 | 1999-07-22 | Cabot Corporation | Multilayer insulation composite |
| CN101224990A (en) * | 2008-01-29 | 2008-07-23 | 中国人民解放军国防科学技术大学 | Ultra-high temperature resistant ceramic matrix composite material and preparation method thereof |
| CN101576179A (en) * | 2009-06-18 | 2009-11-11 | 韦鸿雁 | Multilayered structure and multifunction pipeline and connecting device |
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| CN103727358A (en) | 2014-04-16 |
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