CN103724042A - Preparation method of laminated hybrid heatproof composite structured material - Google Patents
Preparation method of laminated hybrid heatproof composite structured material Download PDFInfo
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- CN103724042A CN103724042A CN201310412273.2A CN201310412273A CN103724042A CN 103724042 A CN103724042 A CN 103724042A CN 201310412273 A CN201310412273 A CN 201310412273A CN 103724042 A CN103724042 A CN 103724042A
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- 238000002360 preparation method Methods 0.000 title claims abstract description 17
- 239000002131 composite material Substances 0.000 title abstract description 20
- 239000000463 material Substances 0.000 title abstract description 17
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 39
- 239000011159 matrix material Substances 0.000 claims abstract description 28
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 23
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 22
- 239000004744 fabric Substances 0.000 claims abstract description 22
- 238000000151 deposition Methods 0.000 claims abstract description 10
- 239000010439 graphite Substances 0.000 claims abstract description 10
- 210000001170 unmyelinated nerve fiber Anatomy 0.000 claims abstract description 10
- 238000000197 pyrolysis Methods 0.000 claims abstract description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 7
- 239000004917 carbon fiber Substances 0.000 claims abstract description 7
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 7
- 239000000126 substance Substances 0.000 claims abstract description 7
- 239000000835 fiber Substances 0.000 claims abstract description 6
- 239000003292 glue Substances 0.000 claims abstract description 6
- 229920001568 phenolic resin Polymers 0.000 claims abstract description 6
- 239000005011 phenolic resin Substances 0.000 claims abstract description 6
- 230000008595 infiltration Effects 0.000 claims abstract description 5
- 238000001764 infiltration Methods 0.000 claims abstract description 5
- 239000007789 gas Substances 0.000 claims description 25
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 21
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 21
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 18
- 229910052786 argon Inorganic materials 0.000 claims description 9
- 229920005989 resin Polymers 0.000 claims description 9
- 239000011347 resin Substances 0.000 claims description 9
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 8
- 239000012159 carrier gas Substances 0.000 claims description 8
- 239000003085 diluting agent Substances 0.000 claims description 8
- 229910052739 hydrogen Inorganic materials 0.000 claims description 8
- 239000001257 hydrogen Substances 0.000 claims description 8
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims description 7
- 230000015572 biosynthetic process Effects 0.000 claims description 6
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 5
- 238000009954 braiding Methods 0.000 claims description 5
- 239000007788 liquid Substances 0.000 claims description 5
- 239000000853 adhesive Substances 0.000 claims description 4
- 230000001070 adhesive effect Effects 0.000 claims description 4
- 239000003795 chemical substances by application Substances 0.000 claims description 4
- 235000009508 confectionery Nutrition 0.000 claims description 4
- 238000003475 lamination Methods 0.000 claims description 4
- 239000003345 natural gas Substances 0.000 claims description 4
- 238000003756 stirring Methods 0.000 claims description 4
- DWAWYEUJUWLESO-UHFFFAOYSA-N trichloromethylsilane Chemical compound [SiH3]C(Cl)(Cl)Cl DWAWYEUJUWLESO-UHFFFAOYSA-N 0.000 claims description 4
- 238000007254 oxidation reaction Methods 0.000 abstract description 11
- 230000003647 oxidation Effects 0.000 abstract description 10
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 3
- 230000008021 deposition Effects 0.000 abstract description 2
- 230000008569 process Effects 0.000 abstract description 2
- 239000002023 wood Substances 0.000 abstract description 2
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical class [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 abstract 3
- 239000000758 substrate Substances 0.000 abstract 2
- 239000011153 ceramic matrix composite Substances 0.000 abstract 1
- 238000007711 solidification Methods 0.000 abstract 1
- 230000008023 solidification Effects 0.000 abstract 1
- 239000010409 thin film Substances 0.000 abstract 1
- 239000000843 powder Substances 0.000 description 12
- 239000011248 coating agent Substances 0.000 description 5
- 238000000576 coating method Methods 0.000 description 5
- 238000010438 heat treatment Methods 0.000 description 4
- 229910017119 AlPO Inorganic materials 0.000 description 3
- OKKJLVBELUTLKV-UHFFFAOYSA-N Methanol Chemical compound OC OKKJLVBELUTLKV-UHFFFAOYSA-N 0.000 description 3
- 241000209456 Plumbago Species 0.000 description 3
- 230000003064 anti-oxidating effect Effects 0.000 description 3
- 150000001722 carbon compounds Chemical class 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 229910052863 mullite Inorganic materials 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 229910016006 MoSi Inorganic materials 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 238000002679 ablation Methods 0.000 description 2
- 230000003078 antioxidant effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 229920003987 resole Polymers 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000004580 weight loss Effects 0.000 description 2
- ZCYVEMRRCGMTRW-UHFFFAOYSA-N 7553-56-2 Chemical compound [I] ZCYVEMRRCGMTRW-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 229920000180 alkyd Polymers 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 235000006708 antioxidants Nutrition 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 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 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 229960000935 dehydrated alcohol Drugs 0.000 description 1
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 235000013312 flour Nutrition 0.000 description 1
- 239000007792 gaseous phase Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 229910052740 iodine Inorganic materials 0.000 description 1
- 239000011630 iodine Substances 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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Abstract
A preparation method of a laminated hybrid heatproof composite structured material is characterized in that graphite is taken as a liner, the surface of the graphite is wound or woven with a C fiber to forma prefabricated part, and C is subjected to deposition and pyrolysis on the prefabricated part so as to form a C/C prefabricated body; a graphite core is removed, carbon cloth or C prepreg is woven on the surface of the prefabricated body, a thin-film pyrolysis C interface is deposited, a SiC matrix is prepared with a CVI (chemical vapor infiltration) method , and a C/SiC composite is formed; and the surface of a wood mold is wound with carbon fiber cloth pre-impregnated in a modified phenolic resin glue solution, then the carbon fiber cloth is matched with the inner diameter of the porous C/C prefabricated part, after hot-press solidification, a phenolic resin matrix composite is formed after demoulding, and the laminated hybrid heatproof composite structured material is obtained. According to the preparation method of the laminated hybrid heatproof composite structured material, a fiber framework is not damaged during the CVI process, and the integrity and strength of the composite are guaranteed; a porous structure in the substrate C/C composite has a heat insulating function, an outer-layer C/SiC ceramic matrix composite performs an oxidation protection function for the substrate C/C composite, and the inner-layer phenolic resin matrix composite improves the overall structural stability of the material; and the preparation technology is simple, and the cost is low.
Description
Technical field
The preparation method who the present invention relates to a kind of resin base and ceramic base hybrid composite, particularly relates to the preparation method that a kind of lamination mixes solar heat protection sandwich.
Background technology
Carbon/carbon (hereinafter to be referred as C/C) matrix material, because it has the characteristic that under low density and excellent mechanical behavior under high temperature, particularly high temperature, mechanical property goes up not down, becomes the preferred material of the thermojunction member of advanced aircraft.But, very easily oxidation under C/C matrix material high temperature, oxidation can make its hole increase, structure weaken, cause the rapid reduction of intensity and other mechanical propertys, and oxidation weight loss 1%, its strength degradation reaches 10%, and (as the Throat Materials for Solid Rocket Motors of Gao Chongzhi ratio, guided missile nose cone etc.) C/C matrix material does not have required high temperature resistance ablation energy ability in extreme environment.Therefore, the high-temp antioxidizing ablation problem of C/C matrix material is the bottleneck of realizing its practical application.Good heat, the chemical stability of mechanical property by comprehensive carbon fiber excellence and ceramic matrix, prepares a kind of by thermal protection, structural bearing and the anti-oxidant new function integrated composite combining for this reason.For anti-oxidation problem, by preparation SiC coating, realize, SiC is outstanding oxidation-resistant material, has good antioxygenation, the SiO of generation
2be the most oxidation resistant known material, protect C/C matrix material by external environment, not to be oxidized when high temperature.And high temperature resistant problem, by improving in conjunction with phenolic resin-base composite, resol good heat resistance, the instantaneous ultrahigh-temperature of ability, and also more excellent through its resistance to elevated temperatures of resol of modification, be widely used in heat-resisting ablator.And its raw material abundance, low price.
Application number is that 201210149453.1 Chinese patent discloses a kind of carbon/carbon compound material SiC/C-AlPO
4the preparation method of-mullite oxidation resistant coating, is mixed to get powder A by silica flour and Graphite Powder 99; By Al
2o
3powder, WO
3powder and B
2o
3powder is mixed to get powder material B; Powder A and powder material B are mixed to get to embedding powder C; Sample is put into plumbago crucible, and add embedding powder C, plumbago crucible is put into vertical vacuum furnace, pass into argon gas and be down to room temperature after as protective atmosphere reacting by heating, after cleaning up in ultrasonic wave with dehydrated alcohol, obtain carbon/carbon compound material silicon carbide transition layer; By C-AlPO
4joining methyl alcohol with mullite powder adds iodine to obtain suspension again, this suspension is placed in water heating kettle, negative electrode is selected the carbon/carbon compound material of having prepared silicon carbide transition layer, sealing water heating kettle also puts it in ultrasonic-microwave producer, deposit rear taking-up sample, be dried to obtain carbon/carbon composite wood SiC/C-AlPO
4-mullite anti-oxidation composite coating.The compound coating of preparation can be protected C/C matrix materials 322 hours at 1500 ℃ of still airs, and oxidation weight loss is less than 2%.
Application number is the preparation method that 200910022719.4 Chinese patent discloses a kind of Improvement of The Oxidation Protective Coating For C/c Composites, treated C/C matrix material is embedded in powder, put into plumbago crucible, at 1800～2200 ℃, carry out processing for 1～3 hour, utilize Supersonic Plasma Spraying equipment by MoSi
2powder sprays to the C/C composite material surface with SiC transition layer, will be prepared with SiC/MoSi
2the C/C matrix material of coating is put into High Temperature Furnaces Heating Apparatus, at 1200～1400 ℃, heat-treats 2～6 hours.The C/C matrix material that the method prepares more than 1650 ℃ in still air anti-oxidization time by prior art, within 200 hours, bring up to 300～400 hours.
Matrix material prepared by above-mentioned two kinds of preparation methods has improved the antioxidant property of C/C matrix material, but high temperature protection problem unresolved.
Summary of the invention
The technical problem to be solved in the present invention is to overcome the deficiencies in the prior art, provide a kind of lamination to mix the preparation method of solar heat protection sandwich, it is characterized in that using graphite as liner, on its surface, be wound around or braiding C fiber formation prefabricated component, and on prefabricated component, deposit pyrolysis C formation porous C/C precast body.Remove graphite core, on precast body surface, be wound around carbon cloth or C preimpregnation cloth, deposition skim pyrolysis C interface, adopts CVI legal system for SiC matrix, forms C/SiC matrix material.The carbon cloth that is wound around preimpregnation modified alkyd resin glue liquid on wooden model surface, then coordinates with porous C/C prefabricated component internal diameter, and after hot-press solidifying, the demoulding forms phenolic resin-base composite.It is characterized in that, comprise the preparation process of following order:
1. using graphite as liner, on its surface, be wound around or braiding C fiber formation prefabricated component;
2. the source of the gas using methane or Sweet natural gas as carbon, hydrogen or argon gas, as diluent gas and carrier gas, are put into cvd furnace by the fiber preform of C described in step 1 and are deposited pyrolysis C matrix, and temperature rise rate is 8～10 ℃/min, depositing temperature is 950～1350 ℃, and depositing time is 50～150h;
3. remove graphite core, obtain porous C/C precast body, and porous insert is carried out to cleaned by ultrasonic vibration 2～4 times, then in 80～120 ℃ of baking ovens, dry 2～4h, until quality no longer changes;
4. on C/C precast body surface, be wound around carbon cloth or C preimpregnation cloth;
5. adopt CVI legal system for SiC matrix, the source of the gas using trichloromethyl silane as SiC, using hydrogen or argon gas as diluent gas and carrier gas, chemical vapor infiltration silicon carbide, CVI temperature is 1000～1300 ℃, the time is 100～350h;
6. use anhydrous alcohol solution modified phenolic resins and solidifying agent, uniform stirring resin glue, lays the carbon fiber of oven dry as in steeping vat, and the resin adhesive liquid configuring is evenly brushed on carbon cloth;
7. on wooden model surface, be wound around C fiber prepreg cloth, then coordinate with porous C/C prefabricated component internal diameter;
8. by porous C/C precast body after treatment step 7, in temperature, be then 120～150 ℃, pressure is 5～15MPa, hot-press solidifying 30～60min;
9. solidify after end the demoulding.
The present invention has advantages of: 1. adopt in chemical gaseous phase permeation process fiber reinforcement is not damaged, guaranteed integrity and the intensity of matrix material; 2. base material C/C matrix material vesicular structure has heat-blocking action; 3. outer C/SiC ceramic matric composite is that base material C/C matrix material plays oxidation protection effect, and internal layer phenolic resin-base composite improves material monolithic structural stability; 4. preparation technology is simple, and cost is low.
Embodiment
Below in conjunction with specific embodiment, further illustrate the present invention, should understand these embodiment 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
1. using graphite as liner, on its surface, be wound around or braiding C fiber formation prefabricated component;
2. the source of the gas using methane or Sweet natural gas as carbon, hydrogen or argon gas, as diluent gas and carrier gas, are put into cvd furnace by the fiber preform of C described in step 1 and are deposited pyrolysis C matrix, and temperature rise rate is 8 ℃/min, depositing temperature is 1150 ℃, and depositing time is 100h;
3. remove graphite core, obtain porous C/C precast body, and porous insert is carried out to cleaned by ultrasonic vibration 2 times, then in 100 ℃ of baking ovens, dry 2h, until quality no longer changes;
4. on C/C precast body surface, be wound around carbon cloth or C preimpregnation cloth;
5. adopt CVI legal system for SiC matrix, the source of the gas using trichloromethyl silane as SiC, using hydrogen or argon gas as diluent gas and carrier gas, chemical vapor infiltration silicon carbide, CVI temperature is 1100 ℃, the time is 250h;
6. use anhydrous alcohol solution modified phenolic resins and solidifying agent, uniform stirring resin glue, lays the carbon fiber of oven dry as in steeping vat, and the resin adhesive liquid configuring is evenly brushed on carbon cloth;
7. on wooden model surface, be wound around C fiber prepreg cloth, then coordinate with porous C/C prefabricated component internal diameter;
8. by porous C/C precast body after treatment step 7, in temperature, be then 130 ℃, pressure is 10MPa, hot-press solidifying 40min;
9. solidify after end the demoulding.
Embodiment 2
1. using graphite as liner, on its surface, be wound around or braiding C fiber formation prefabricated component;
2. the source of the gas using methane or Sweet natural gas as carbon, hydrogen or argon gas, as diluent gas and carrier gas, are put into cvd furnace by the fiber preform of C described in step 1 and are deposited pyrolysis C matrix, and temperature rise rate is 10 ℃/min, depositing temperature is 1150 ℃, and depositing time is 150h;
3. remove graphite core, obtain porous C/C precast body, and porous insert is carried out to cleaned by ultrasonic vibration 3 times, then in 120 ℃ of baking ovens, dry 3h, until quality no longer changes;
4. on C/C precast body surface, be wound around carbon cloth or C preimpregnation cloth;
5. adopt CVI legal system for SiC matrix, the source of the gas using trichloromethyl silane as SiC, using hydrogen or argon gas as diluent gas and carrier gas, chemical vapor infiltration silicon carbide, CVI temperature is 1200 ℃, the time is 300h;
6. use anhydrous alcohol solution modified phenolic resins and solidifying agent, uniform stirring resin glue, lays the carbon fiber of oven dry as in steeping vat, and the resin adhesive liquid configuring is evenly brushed on carbon cloth;
7. on wooden model surface, be wound around C fiber prepreg cloth, then coordinate with porous C/C prefabricated component internal diameter;
8. by porous C/C precast body after treatment step 7, in temperature, be then 140 ℃, pressure is 12MPa, hot-press solidifying 50min;
9. solidify after end the demoulding.
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 (1)
1. lamination mixes a preparation method for solar heat protection sandwich, it is characterized in that comprising the preparation process of following order:
1. using graphite as liner, on its surface, be wound around or braiding C fiber formation prefabricated component;
2. the source of the gas using methane or Sweet natural gas as carbon, hydrogen or argon gas, as diluent gas and carrier gas, are put into cvd furnace by the fiber preform of C described in step 1 and are deposited pyrolysis C matrix, and temperature rise rate is 8～10 ℃/min, depositing temperature is 950～1350 ℃, and depositing time is 50～150h;
3. remove graphite core, obtain porous C/C precast body, and porous insert is carried out to cleaned by ultrasonic vibration 2～4 times, then in 80～120 ℃ of baking ovens, dry 2～4h, until quality no longer changes;
4. on C/C precast body surface, be wound around carbon cloth or C preimpregnation cloth;
5. adopt CVI legal system for SiC matrix, the source of the gas using trichloromethyl silane as SiC, using hydrogen or argon gas as diluent gas and carrier gas, chemical vapor infiltration silicon carbide, CVI temperature is 1000～1300 ℃, the time is 100～350h;
6. use anhydrous alcohol solution modified phenolic resins and solidifying agent, uniform stirring resin glue, lays the carbon fiber of oven dry as in steeping vat, and the resin adhesive liquid configuring is evenly brushed on carbon cloth;
7. on wooden model surface, be wound around C fiber prepreg cloth, then coordinate with porous C/C prefabricated component internal diameter;
8. by porous C/C precast body after treatment step 7, in temperature, be then 120～150 ℃, pressure is 5～15MPa, hot-press solidifying 30～60min;
9. solidify after end the demoulding.
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| CN201310412273.2A CN103724042B (en) | 2013-09-11 | 2013-09-11 | A kind of lamination mixes the preparation method of solar heat protection sandwich |
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| CN201310412273.2A CN103724042B (en) | 2013-09-11 | 2013-09-11 | A kind of lamination mixes the preparation method of solar heat protection sandwich |
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| CN103724042B CN103724042B (en) | 2015-08-26 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103954131A (en) * | 2014-04-17 | 2014-07-30 | 四川科达节能技术有限公司 | Inner liner material for industrial kiln furnace |
| TWI602794B (en) * | 2016-03-14 | 2017-10-21 | National Chung-Shan Institute Of Science And Tech | Ceramic composite materials production methods |
| CN107417277A (en) * | 2017-07-24 | 2017-12-01 | 西北工业大学 | A kind of porous carbon materials are heat-insulated with the standby method of anti-oxidant coordinate system |
| CN108484135A (en) * | 2018-04-17 | 2018-09-04 | 苏州宏久航空防热材料科技有限公司 | A kind of growth in situ ceramics reinforcing fiber resin composite materials |
| CN108794040A (en) * | 2018-06-29 | 2018-11-13 | 航天材料及工艺研究所 | It is a kind of based on the melting composite material of siliconizing treatment processes, carbon/carbon porous body and preparation method thereof |
| CN111164061A (en) * | 2017-10-02 | 2020-05-15 | 赛峰集团陶瓷 | Method for manufacturing a hollow component made of ceramic matrix composite material |
| CN111875402A (en) * | 2020-07-23 | 2020-11-03 | 西安超码科技有限公司 | Fiber winding reinforced graphite heating tube structure and preparation method thereof |
| CN113149684A (en) * | 2021-04-29 | 2021-07-23 | 上海骐杰碳素材料有限公司 | Carbon-carbon or carbon-ceramic composite material winding preform, product and preparation method thereof |
| CN113979771A (en) * | 2021-10-19 | 2022-01-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Sandwich structure ceramic matrix composite material containing heat conduction layer and preparation method |
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| CN102944320A (en) * | 2012-12-03 | 2013-02-27 | 中国航空工业集团公司北京长城计量测试技术研究所 | Cooling-free type high temperature sensor based on composite material |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103954131A (en) * | 2014-04-17 | 2014-07-30 | 四川科达节能技术有限公司 | Inner liner material for industrial kiln furnace |
| TWI602794B (en) * | 2016-03-14 | 2017-10-21 | National Chung-Shan Institute Of Science And Tech | Ceramic composite materials production methods |
| CN107417277A (en) * | 2017-07-24 | 2017-12-01 | 西北工业大学 | A kind of porous carbon materials are heat-insulated with the standby method of anti-oxidant coordinate system |
| CN107417277B (en) * | 2017-07-24 | 2020-06-16 | 西北工业大学 | Method for synergistically preparing heat insulation and antioxidation of porous carbon material |
| CN111164061A (en) * | 2017-10-02 | 2020-05-15 | 赛峰集团陶瓷 | Method for manufacturing a hollow component made of ceramic matrix composite material |
| US11608299B2 (en) | 2017-10-02 | 2023-03-21 | Safran Ceramics | Method for producing a hollow part made of a ceramic matrix composite material |
| CN108484135A (en) * | 2018-04-17 | 2018-09-04 | 苏州宏久航空防热材料科技有限公司 | A kind of growth in situ ceramics reinforcing fiber resin composite materials |
| CN108794040A (en) * | 2018-06-29 | 2018-11-13 | 航天材料及工艺研究所 | It is a kind of based on the melting composite material of siliconizing treatment processes, carbon/carbon porous body and preparation method thereof |
| CN111875402A (en) * | 2020-07-23 | 2020-11-03 | 西安超码科技有限公司 | Fiber winding reinforced graphite heating tube structure and preparation method thereof |
| CN113149684A (en) * | 2021-04-29 | 2021-07-23 | 上海骐杰碳素材料有限公司 | Carbon-carbon or carbon-ceramic composite material winding preform, product and preparation method thereof |
| CN113979771A (en) * | 2021-10-19 | 2022-01-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Sandwich structure ceramic matrix composite material containing heat conduction layer and preparation method |
| CN113979771B (en) * | 2021-10-19 | 2022-10-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Sandwich structure ceramic matrix composite containing heat conduction layer and preparation method thereof |
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Address after: 215400 Chengxiang City, Taicang Province town of the People South Road, No. 162, No. Patentee after: TAICANG PAIOU TECHNICAL ADVISORY SERVICE Co.,Ltd. Address before: 215400 people's road, Jiangsu, Taicang Hua Xu apartment C412 Patentee before: TAICANG PAIOU TECHNICAL ADVISORY SERVICE Co.,Ltd. |
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