CN103722786A - Laminated hybrid heatproof composite structured material - Google Patents
Laminated hybrid heatproof composite structured material Download PDFInfo
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- CN103722786A CN103722786A CN201310412275.1A CN201310412275A CN103722786A CN 103722786 A CN103722786 A CN 103722786A CN 201310412275 A CN201310412275 A CN 201310412275A CN 103722786 A CN103722786 A CN 103722786A
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Abstract
A laminated hybrid heatproof composite structured material is characterized in that the composite structured material adopts a hollow round tube shape and is formed by three layers of different composites, wherein the inner layer is a phenolic resin matrix composite, the middle layer is a porous C/C composite, the outer layer is a C/SiC ceramic matrix composite, and each of C fiber in the C/SiC ceramic matrix composite and matrix C in the porous C/C composite is provided with a layer of pyrolysis C interface or a ZrO2 and BN interface. A porous structure in the substrate C/C composite has a heat insulating function, and the composite structured material has a lighter overall mass; phenolic resin is cheap, so that the composite structured material has low cost; and the outer-layer C/SiC ceramic matrix composite performs an oxidation protection function for the substrate C/C composite, and filled resin improves overall structural stability of the material.
Description
Technical field
The present invention relates to a kind of resin-based and ceramic base hybrid composite, particularly relate to a kind of lamination and mix solar heat protection sandwich.
Background technology
Carbon/carbon (hereinafter to be referred as C/C) composite, 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 composite high temperature, oxidation can make its hole increase, structure weaken, cause the rapid reduction of intensity and other mechanical performances, and oxidation weight loss 1%, its intensity declines and reaches 10%, and (as the Throat Materials for Solid Rocket Motors of Gao Chongzhi ratio, guided missile nose cone etc.) C/C composite does not have required high temperature resistance ablation energy ability in extreme environment.Therefore, the high-temp antioxidizing ablation problem of C/C composite 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 antioxidation, the SiO of generation
2be the most oxidation resistant known material, protect C/C composite by external environment, not to be oxidized when high temperature.And high temperature resistant problem, by improving in conjunction with phenolic resin-base composite, phenolic resins good heat resistance, the instantaneous superhigh temperature of ability, and also more excellent through its resistance to elevated temperatures of phenolic resins of modification, be widely used in heat-resisting ablator.And its raw material abundance, low price.
Application number is that 201310007876.4 Chinese patent discloses a kind of preparing low-density carbon/carbon composite C/SiC composite coating and preparation technology thereof, and this composite coating is comprised of interior sealing of hole layer and external coating two parts; Described interior sealing of hole layer is made by the raw material of following percentage by weight; Carborundum powder 10%～60%, silica flour 1%～25%, graphite powder 0.05%～8%, polyacrylonitrile milled carbon fiber 1%～10%, Ludox 40%～80%; Described external coating is made by the raw material of following percentage by weight: carborundum powder 10%～30%, resin 40%～60%, diluent 30%～70%, curing agent 1%～6%.The present invention also comprises the preparation technology of described preparing low-density carbon/carbon composite C/SiC composite coating.The present invention's preparing low-density carbon/carbon composite C/SiC composite coating has better oxidation resistance, and the adhesion of coating and matrix material is good, surface compact, and flawless produces, without powder falling phenomenon.
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 composite is embedded in powder, put into graphite 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 zone, will be prepared with SiC/MoSi
2the C/C composite of coating is put into high temperature furnace, at 1200～1400 ℃, heat-treats 2～6 hours.The C/C composite 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.
Composite prepared by above-mentioned two kinds of preparation methods has improved the antioxygenic property of C/C composite, 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 solar heat protection sandwich, it is characterized in that, described sandwich is open circles tubulose, three layers of different composite, consist of, internal layer is phenolic resin-base composite, and intermediate layer is porous C/C composite, skin is C/SiC ceramic matric composite, and in C/SiC composite, in C fiber and porous C/C composite, matrix C has one deck pyrolysis C interface or ZrO
2, BN interface.
Intermediate layer of the present invention porous C/C composite material by adopting CVI method makes, and wild phase Two-dimensional Carbon fiber cloth volume fraction is 30～45%, is the base material that this lamination providing mixes solar heat protection sandwich.
Internal layer phenolic resin-base composite of the present invention is that phenolic resins take modification is as matrix, Two-dimensional Carbon fiber cloth is reinforcing material, and carbon cloth volume fraction is 30～45%, and hot-press solidifying obtains, thickness is 2～4mm, and paving overlays on C/C composite inwall.
Outer C/SiC ceramic matric composite of the present invention is take carborundum as matrix, and two-dimensional fiber cloth is reinforcing material, and carbon cloth volume fraction is 30～45%, adopts chemical vapor infiltration to prepare, and thickness is 1～3mm.C/SiC ceramic matric composite, at C/C composite outer wall, has effectively improved the antioxygenic property of C/C composite.
The present invention has advantages of: 1. base material C/C composite loose structure has heat-blocking action, and sandwich total quality is lighter; 2. phenolic resins low price, sandwich cost is low; 3. outer C/SiC ceramic matric composite is that base material C/C composite plays oxidation protection effect, and potting resin improves material monolithic structural stability.
Accompanying drawing explanation
Fig. 1 is that lamination mixes solar heat protection sandwich longitdinal cross-section diagram
Diagram 10 is porous C/C composite; 20 is C/SiC composite; 30 is phenolic resin-base composite
Fig. 2 is that lamination mixes solar heat protection sandwich view in transverse section
Diagram 10 is porous C/C composite; 20 is C/SiC composite: 30 is phenolic resin-base composite
The specific 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
With reference to Fig. 1 lamination, mix solar heat protection sandwich longitdinal cross-section diagram, wherein 10 is porous C/C composite, and 20 is C/SiC composite, and 30 is phenolic resin-base composite.Sandwich is open circles tubulose, comprises phenolic resin-base composite, porous C/C composite, C/SiC ceramic matric composite.Internal layer is phenolic resin-base composite, and wild phase Two-dimensional Carbon fiber volume fraction is 40%, thickness 2mm.Intermediate layer is porous C/C composite, and wild phase Two-dimensional Carbon fiber volume fraction is 45%.Skin is C/SiC ceramic matric composite, and wild phase Two-dimensional Carbon fiber volume fraction is 35%, and thickness is 3mm.In C/SiC composite, in C fiber and porous C/C composite, matrix C has one deck pyrolysis C interface or ZrO
2, BN interface.
Embodiment 2
With reference to Fig. 1 lamination, mix solar heat protection sandwich longitdinal cross-section diagram, wherein 10 is porous C/C composite, and 20 is C/SiC composite, and 30 is phenolic resin-base composite.Sandwich is open circles tubulose, comprises phenolic resin-base composite, porous C/C composite, C/SiC ceramic matric composite.Internal layer is phenolic resin-base composite, and wild phase Two-dimensional Carbon fiber volume fraction is 35%, thickness 3mm.Intermediate layer is porous C/C composite, and wild phase Two-dimensional Carbon fiber volume fraction is 40%.Skin is C/SiC ceramic matric composite, and wild phase Two-dimensional Carbon fiber volume fraction is 40%, and thickness is 2mm.In C/SiC composite, in C fiber and porous C/C composite, matrix C has one deck pyrolysis C interface or ZrO
2, BN interface.
Above are only two specific embodiment 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 (4)
1. lamination mixes a solar heat protection sandwich, it is characterized in that comprising phenolic resin-base composite, porous C/C composite, C/SiC ceramic matric composite.
2. sandwich according to claim 1, is characterized in that described porous C/C composite material by adopting CVI method makes, and wild phase Two-dimensional Carbon fiber cloth volume fraction is 30～45%.
3. sandwich according to claim 1, it is characterized in that described phenolic resin-base composite is positioned at the inwall of C/C composite, take the phenolic resins of modification as matrix, Two-dimensional Carbon fiber cloth is reinforcing material, carbon cloth volume fraction is 30～45%, and thickness is 2～4mm.
4. sandwich according to claim 1, it is characterized in that described C/SiC ceramic matric composite is positioned at the outer wall of C/C composite, take carborundum as matrix, two-dimensional fiber cloth is reinforcing material, carbon cloth volume fraction is 30～45%, and thickness is 1～3mm.
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| CN201310412275.1A CN103722786A (en) | 2013-09-11 | 2013-09-11 | Laminated hybrid heatproof composite structured material |
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| CN201310412275.1A CN103722786A (en) | 2013-09-11 | 2013-09-11 | Laminated hybrid heatproof composite structured material |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106584942A (en) * | 2016-12-07 | 2017-04-26 | 航天特种材料及工艺技术研究所 | External thermal insulation material and preparation method thereof |
| CN107266075A (en) * | 2017-07-03 | 2017-10-20 | 湖南工业大学 | A kind of C/C SiC ceramic matrix composite materials and its preparation method and application |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1850730A (en) * | 2006-05-26 | 2006-10-25 | 中国科学院上海硅酸盐研究所 | Method for preparing carbon-fiber reinforced silicon carbonate base composite by gas-phase siliconizing technology |
| CN101224989A (en) * | 2008-01-29 | 2008-07-23 | 中国人民解放军国防科学技术大学 | Two-dimensional fiber cloth reinforced composite material and preparation method thereof |
| US20100003504A1 (en) * | 2006-12-18 | 2010-01-07 | Snecma Propulsion Solide | Composite material part with a silicon-containing ceramic matrix protected against corrosion |
| CN102010231A (en) * | 2010-10-24 | 2011-04-13 | 西安超码科技有限公司 | Method for preparing low-density carbon/carbon composite material surface coating |
| CN102976756A (en) * | 2012-04-19 | 2013-03-20 | 安徽众星新材料有限公司 | Continuous carbon fiber reinforced C-SiC binary base composite material and preparation method thereof |
| CN103058712A (en) * | 2013-01-10 | 2013-04-24 | 湖南南方搏云新材料有限责任公司 | C/SiC composite coating applied to surface of low-density carbon/carbon composite material and preparation process thereof |
-
2013
- 2013-09-11 CN CN201310412275.1A patent/CN103722786A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1850730A (en) * | 2006-05-26 | 2006-10-25 | 中国科学院上海硅酸盐研究所 | Method for preparing carbon-fiber reinforced silicon carbonate base composite by gas-phase siliconizing technology |
| US20100003504A1 (en) * | 2006-12-18 | 2010-01-07 | Snecma Propulsion Solide | Composite material part with a silicon-containing ceramic matrix protected against corrosion |
| CN101224989A (en) * | 2008-01-29 | 2008-07-23 | 中国人民解放军国防科学技术大学 | Two-dimensional fiber cloth reinforced composite material and preparation method thereof |
| CN102010231A (en) * | 2010-10-24 | 2011-04-13 | 西安超码科技有限公司 | Method for preparing low-density carbon/carbon composite material surface coating |
| CN102976756A (en) * | 2012-04-19 | 2013-03-20 | 安徽众星新材料有限公司 | Continuous carbon fiber reinforced C-SiC binary base composite material and preparation method thereof |
| CN103058712A (en) * | 2013-01-10 | 2013-04-24 | 湖南南方搏云新材料有限责任公司 | C/SiC composite coating applied to surface of low-density carbon/carbon composite material and preparation process thereof |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106584942A (en) * | 2016-12-07 | 2017-04-26 | 航天特种材料及工艺技术研究所 | External thermal insulation material and preparation method thereof |
| CN106584942B (en) * | 2016-12-07 | 2017-11-14 | 航天特种材料及工艺技术研究所 | A kind of outer heat insulation material and preparation method thereof |
| CN107266075A (en) * | 2017-07-03 | 2017-10-20 | 湖南工业大学 | A kind of C/C SiC ceramic matrix composite materials and its preparation method and application |
| CN107266075B (en) * | 2017-07-03 | 2020-10-02 | 湖南工业大学 | C/C-SiC composite material and preparation method and application thereof |
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Application publication date: 20140416 |