CN108794039A - A kind of composite modified basis material of charcoal/charcoal and its preparation process - Google Patents
A kind of composite modified basis material of charcoal/charcoal and its preparation process Download PDFInfo
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- CN108794039A CN108794039A CN201810601977.7A CN201810601977A CN108794039A CN 108794039 A CN108794039 A CN 108794039A CN 201810601977 A CN201810601977 A CN 201810601977A CN 108794039 A CN108794039 A CN 108794039A
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
- C04B35/83—Carbon fibres in a carbon matrix
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
- C04B41/52—Multiple coating or impregnating multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
- C04B41/81—Coating or impregnation
- C04B41/89—Coating or impregnation for obtaining at least two superposed coatings having different compositions
Abstract
The invention discloses a kind of composite modified basis material of charcoal/charcoal and its preparation process, that ablation humidification is played in C/C composite materials has SiC, ZrC, pyrolytic carbon and Carbon fibe；Pyrolytic carbon is wrapped on fiber reinforcement, and SiC is uniformly enclosed in around pyrolytic carbon, and ZrC is evenly distributed in intrinsic silicon as the main phase that matrix is filled；SiC and ZrC is formed by following mass percentage composition ingredient：80~95% Zr powder, 5~20% Si powder and 0~5% C powder mixing；The preparation process of the present invention comprises the following steps that：C/C green bodies pre-process；The preparation of Zr-Si-C mixed-powders；Vacuum carbon tube furnace high-temperature process；Molded part stress relief is heat-treated；Oxy-acetylene flame ablation instrument carries out the ablation property examination of coating.The modified C/C composite materials of present invention reaction infiltration are increased to 150s in 3000 DEG C or so oxy-acetylene flame ablation times and material overall structure is not destroyed.
Description
Technical field
The present invention relates to Material Field, a kind of composite modified basis material of charcoal/charcoal and its preparation process are referred in particular to.
Background technology
C/C composite materials with excellent properties such as its low-density, high specific strength, high ratio modulus, resistance to ablation and heat shock resistances
As one of preferred material in aerospace field.But C/C composite materials start rapid oxidation, oxygen for 400 DEG C or more in air
Change process and under the catalytic action of contaminant particles, passes through material along with the flowing of the oxygen in gas medium from material boundary
Material surface pore diffuses to inside, and the C/C composite materials for causing its performance to decay rapidly, therefore not being modified are difficult to exist for a long time
High temperature is born in non-vacuum environment, high-velocity particles stream washes away.By introducing superhigh temperature ceramics (Ultral-high
Temperature ceramic) such as SiC and ZrC be a kind of effective way of C/C composite materials ablation resistance.It is current to prepare
The method of C/C-SiC-ZrC composite materials has precursor infiltration and pyrolysis (PIP), plasma spraying (PS), chemical vapor deposition
The methods of (CVD) and react infiltration (RMI), it does not obviously fail within the scope of 3000 DEG C or so 30s of material, but at 3000 DEG C or more
The ablation resistance of longer time is still undecided.
Document 1：" zircon sand embeds graphite method and prepares ZrC-SiC composite coatings, Journal of Inorganic Materials, 2010 (25), P41-
46. " disclose a kind of a kind of method preparing carbon-carbon composites anti-yaw damper coating using zircon sand investment, and this method can be with
Prepare a kind of mixed coating that ZrC and SiC crystal grain is mutually mixed.This method is disadvantageous in that coating prepared by investment causes
Density is not high enough there are gap and micro-crack, and preparation technology of coating is unstable, and the anti-yaw damper temperature of coating is only on 1900 DEG C of left sides
It is right.
Document 2：" hypersonic vehicle C/SiC-ZrC Compound Material Engineerings and ablation property research [J] rocket propulsions,
2017 (3), 59-66. " describe the preparation method of C/C-ZrC-SiC composite materials, analyze the excellent of various preparation methods and lack
Point, the CVI+PIP hybrid techniques especially to get up to common PIP methods and new development are introduced.Document is pointed out to use
Although single PIP methods or CVI+PIP methods can prepare highdensity C/ZrC-SiC composite materials, during PIP
A certain amount of Zr powder or Si powder can be remained, free Zr/Si powder inevitably reacts with carbon fiber, causes reinforced phase carbon
The damage of fiber causes carbon fiber-reinforced strengthening action to reduce, to make the comprehensive performance of material decline, especially mechanical strength
It is greatly reduced, material calamity is caused to be broken.Meanwhile technological process is complicated, needs to impregnate repeatedly repeatedly.
Document 3："Microstructures and Ablation Resistance of ZrC Coating for
SiC-Coated Carbon/Carbon Composites Prepared by Supersonic Plasma
Spraying.Journal of Thermal Spray Technology, 2011 (2), P1286-1291. " are described in C/C-
Plasma spraying ZrC coatings, but Supersonic Plasma Spraying layer (ZrC) and matrix (SiC- in text are used in SiC material again
Coated C/C materials) between thermal stress be greater than reaction infiltration method or the material that is prepared of precursor synthesis method method, and apply
Combination between layer and matrix is mainly the mechanical bond of the percussion in spraying process, rather than answers infiltration method obtained
Metallurgical binding.In addition, the ablation examination of material is carried out in high heat flux density shock environment, it can be further exacerbated by coating in this way
Increase with matrix thermal stress is so as to cause failure.
Document 4："Ablation resistance of ZrC/SiC gradient coating for SiC-coated
carbon/carbon composites prepared by supersonic plasma spraying,Journal of
The European Ceramic Society, 2016 (2), P3739-3746. " are described in C/C-SiC composite material surfaces
On the technique of ZrC/SiC coatings is prepared using supersonic spray coating method, although theoretically between coating ZrC/SiC and C/C-SiC
Coefficient of thermal expansion be that a gradient is excessive, being capable of relief of thermal stress.But Supersonic Plasma Spraying method relative response infiltration method
Its coating and matrix stress are big, in conjunction with force difference, and the used brittleness of dusty spray is big, binding force is low ceramic powders ZrC and
SiC.Dusty spray there is a kind of thermal mismatching in melting spraying process in this way, then sprays to and is combined rear thermal mismatching with matrix
It can be further exacerbated by, to reduce the resistance to ablation of material.
Also, the ablative cork coatings that above-mentioned all documents are provided are exactly anchoring strength of coating there are a common defect
It is weaker, it in the case where high-speed flow washes away environment, is easy to fall off and coating failure, material, which will fail that matrix can not be formed, to be protected.
Invention content
The technical problem to be solved by the present invention is in view of the above shortcomings of the prior art, provide one kind in 3000 DEG C or so oxygen
The composite modified basis material of charcoal/charcoal and its system that the acetylene flame ablation time is increased to 150s and material overall structure is not destroyed
Standby technique.
The technical solution adopted by the present invention is as follows：A kind of composite modified basis material of charcoal/charcoal, including Carbon fibe layer, pyrolysis
Layer of charcoal, SiC layer and ZrC layer, wherein above-mentioned pyrolysis layer of charcoal is covered in the surface of Carbon fibe layer, and SiC layer is covered in pyrolysis layer of charcoal table
Face, ZrC layers are covered in SiC layer surface；Above-mentioned pyrolysis layer of charcoal alleviates the thermal stress between Carbon fibe and SiC layer, and SiC layer alleviates heat
Thermal stress between layer of charcoal and ZrC layers is solved, makes pyrolysis layer of charcoal, SiC layer and ZrC layers not fallen off in ablation environment；Above-mentioned SiC layer and
ZrC layers include element：Zr, Si and C, and mass percentage composition is：80~95%Zr powder, 5~20%Si powder and 0~5%C
Powder.
A kind of preparation process of the composite modified basis material of charcoal/charcoal, comprises the following steps that：
(a) preparation of infiltrant：Weigh 80~95%Zr powder, 5~20%Si powder and 0~5%C respectively by mass fraction
Powder, then infiltrant is made using 1~3h of rotating speed 200~250r/min ball millings；
(b) preparation of Carbon fibe/pyrolytic carbon/SiC/ZrC composite materials：C/C is completely covered in infiltrant in step (a)
It is put into graphite crucible after matrix, then graphite crucible is put into vacuum drying oven, be passed through the guarantor that flow is 500~600ml/min
Furnace temperature is risen to 1800~2000 DEG C with the heating rate of 7.5~12.5 DEG C/min, 1~3h is kept the temperature, then with 7 by shield property gas
Furnace temperature is down to 1000~1200 DEG C by the cooling rate of~10 DEG C/min, is closed power supply and is naturally cooling to room temperature, in C/C matrix materials
Material is internal to form the anti-yaw damper carbon carbon composite with Carbon fibe/pyrolytic carbon/SiC/ZrC gradient-structures；
(c) Carbon fibe/pyrolytic carbon/SiC/ZrC composite inner structural stresses are alleviated：It will be prepared in step (b)
Carbon fibe/pyrolytic carbon/SiC/ZrC composite materials be put into high temperature furnace, furnace temperature is risen to the heating rate of 7~10 DEG C/min
1500~1800 DEG C, 1~3h is kept the temperature, closing power supply with furnace cooling is naturally cooling to room temperature, obtains sample；
(d) oxy-acetylene flame ablation instrument is used to carry out ablation property test：Sample in step c is positioned over equipped with cooling
On the objective table of system, use ablation rifle nozzle diameter for 2mm, distance of the sample initial surface away from flame-thrower nozzle be 9.8~
10.2mm, flame ablation angle are 90 ° of progress ablation property tests.
Preferably, specific oxy-acetylene flame burning candle experiment parameter is in the step d：O2Flow 1512L/h, C2H2Stream
Measure 1116L/h, O2Atmospheric pressure 0.4Mpa, C2H2Atmospheric pressure 0.095Mpa.
The beneficial effects of the present invention are：
That ablation humidification is played in C/C composite materials of the present invention has SiC, ZrC, pyrolytic carbon and Carbon fibe；Pyrolytic carbon
It is wrapped on fiber reinforcement, SiC is uniformly enclosed in around pyrolytic carbon, and ZrC is evenly distributed in as the main phase that matrix is filled
Intrinsic silicon；Wherein, above-mentioned SiC and ZrC is formed by following mass percentage composition ingredient：80~95%Zr powder, 5~20%
Si powder and the mixing of 0~5%C powder；The C/C of resistance to ablation composite material preparation process, comprises the following steps that：C/C green bodies pre-process；
The preparation of Zr-Si-C mixed powders；Vacuum carbon tube furnace high-temperature process；Molded part stress relief is heat-treated；Oxy-acetylene flame ablation instrument into
The ablation property of row coating is examined.The present invention reacts the modified C/C composite materials of infiltration and is burnt in 3000 DEG C or so oxy-acetylene flames
The erosion time is increased to 150s from traditional 30s and material overall structure is not destroyed.
Description of the drawings
Fig. 1 is the composite modified basis material scanning electron microscope schematic diagram of charcoal/charcoal prepared by the embodiment of the present invention 1.
Fig. 2 is the composite modified basis material scanning electron microscope backscattered electron signal of charcoal/charcoal prepared by the embodiment of the present invention 2
Figure.
Fig. 3 is the cross section structure schematic diagram of the matrix model of the composite modified basis material of charcoal/charcoal of the present invention.
Fig. 4 is the details enlarged structure schematic diagram of Fig. 3.
Fig. 5 is the XRD result figures of the composite modified basis material of charcoal/charcoal of the present invention.
Specific implementation mode
Below in conjunction with attached drawing, the invention will be further described：
Embodiment 1：As shown in Fig. 1, Fig. 3, Fig. 4, Fig. 5：By charcoal charcoal green body respectively with No. 1000, No. 1500 and No. 2000 sand
Distilled water and washes of absolute alcohol are used after paper sanding and polishing, it is spare after dry；Weigh the powder of 90%Zr respectively by mass fraction,
The powder of 7%Si, the embedding powder used in reaction infiltration is made in 2%C spheres of powder mill 10h, at prepared embedding powder and prognosis
The charcoal charcoal green body of reason is put into graphite crucible or graphite paper reactor；Graphite crucible is put into the vertical vacuum furnace of graphite heater
In, vacuum degree reaches 5 × 10-3After Pa, furnace temperature is risen to 1800 DEG C with the heating rate of 7.5 DEG C/min, 3h is kept the temperature, then with 10
DEG C/furnace temperature is down to 1200 DEG C by the cooling rate of min, it closes power supply and is naturally cooling to room temperature, formed inside C/C basis materials
Anti-yaw damper interior substructure with ZrC-SiC-C ceramic phases.
Modification C/C composite materials after infiltration is reacted, which are put into high temperature furnace, to be heat-treated, with the heating speed of 7 DEG C/min
Furnace temperature is risen to 1200 DEG C by degree, keeps the temperature 4h, and it is natural then to be closed power supply near 500 DEG C of furnace temperature with the cooling rate of 30 DEG C/h
It is cooled to room temperature, to eliminate the residual thermal stress in infiltration matrix.
The ablation property test of coating is carried out using oxy-acetylene flame ablation instrument, sample is positioned over the loading equipped with cooling system
On platform, ablation rifle nozzle diameter is 2mm, and distance of the sample initial surface away from flame-thrower nozzle is 10 ± 0.2mm, flame ablation angle
It is 90 °.Specific oxy-acetylene flame burns candle experiment parameter：O2Flow 1512L/h, C2H2Flow 1116L/h, O2Atmospheric pressure 0.4Mpa,
C2H2Atmospheric pressure 0.095Mpa.
After tested, the prepared C/C composite materials ceramic matrix of resistance to ablation layer is in 3000 DEG C or so oxy-acetylene flame ablations
Between be increased to 150s and apparent structure does not occur and destroys for matrix, therefore modified C/C composite materials are in 3000 DEG C of oxygen-containing conditions
Stabilization resistance to ablation ability with 150s down.
It can see from the ablative cork coatings surface scan electromicroscopic photograph of Fig. 1, serious structure does not occur for intrinsic silicon
It destroys, without cracked and hole.
Embodiment 2：By C/C basis materials respectively with No. 1000, No. 1500 and No. 2000 as shown in Fig. 2, Fig. 3, Fig. 4, Fig. 5
Distilled water and washes of absolute alcohol are used after sand paper sanding and polishing, it is spare after dry；Weigh 96%Zr powder respectively by mass fraction,
3%Si powder, the 1%C spheres of powder mill 10h be made reaction infiltration used in embedding powder, by prepared embedding powder with it is pretreated
Charcoal charcoal green body is put into graphite crucible or graphite paper reactor；Graphite crucible is put into the vertical vacuum furnace of graphite heater,
Vacuum degree reaches 5 × 10-3After Pa, furnace temperature is risen to 1800 DEG C with the heating rate of 7.5 DEG C/min, keeps the temperature 3h, then with 10 DEG C/
Furnace temperature is down to 1200 DEG C by the cooling rate of min, is closed power supply and is naturally cooling to room temperature, forms tool inside C/C basis materials
There is the anti-yaw damper interior substructure of ZrC-SiC-C ceramic phases.
Modification C/C composite materials after infiltration is reacted, which are put into high temperature furnace, to be heat-treated, with the heating speed of 7 DEG C/min
Furnace temperature is risen to 1200 DEG C by degree, keeps the temperature 4h, and it is natural then to be closed power supply near 500 DEG C of furnace temperature with the cooling rate of 30 DEG C/h
It is cooled to room temperature, to eliminate the residual thermal stress in infiltration matrix.
The ablation property test of coating is carried out using oxy-acetylene flame ablation instrument, sample is positioned over the loading equipped with cooling system
On platform, ablation rifle nozzle diameter is 2mm, and distance of the sample initial surface away from flame-thrower nozzle is 10 ± 0.2mm, flame ablation angle
It is 90 °.Specific oxy-acetylene flame burns candle experiment parameter：O2Flow 1512L/h, C2H2Flow 1116L/h, O2Atmospheric pressure 0.4Mpa,
C2H2Atmospheric pressure 0.095Mpa.
After tested, the prepared C/C composite materials ceramic matrix of resistance to ablation layer is in 3000 DEG C or so oxy-acetylene flame ablations
Between be increased to 90s and apparent structure does not occur and destroys for matrix, therefore there is C/C composite materials 90s to stablize resistance to ablation ability.
It can see from the ablative cork coatings surface scan electromicroscopic photograph of Fig. 2, serious structure does not occur for intrinsic silicon
It destroys, without cracked and hole.
Embodiment 3：By C/C basis materials respectively with after No. 1000, No. 1500 and No. 2000 sand paper sanding and polishings with distillation
Water and washes of absolute alcohol, it is spare after dry；Weigh 75%Zr powder, 20%Si powder respectively by mass fraction, the 5%C spheres of powder grind 10h
The embedding powder used in reaction infiltration is made, by prepared embedding powder and pretreated charcoal charcoal green body be put into graphite crucible or
In graphite paper reactor；Graphite crucible is put into the vertical vacuum furnace of graphite heater, vacuum degree reaches 5 × 10-3After Pa, with
Furnace temperature is risen to 1800 DEG C by the heating rate of 7.5 DEG C/min, is kept the temperature 3h, is then down to furnace temperature with the cooling rate of 10 DEG C/min
It 1200 DEG C, closes power supply and is naturally cooling to room temperature, form the anti-burning with ZrC-SiC-C ceramic phases inside C/C basis materials
Lose interior substructure.
Modification C/C composite materials after infiltration is reacted, which are put into high temperature furnace, to be heat-treated, with the heating speed of 7 DEG C/min
Furnace temperature is risen to 1200 DEG C by degree, keeps the temperature 4h, and it is natural then to be closed power supply near 500 DEG C of furnace temperature with the cooling rate of 30 DEG C/h
It is cooled to room temperature, to eliminate the residual thermal stress in infiltration matrix.
The ablation property test of coating is carried out using oxy-acetylene flame ablation instrument, sample is positioned over the loading equipped with cooling system
On platform, ablation rifle nozzle diameter is 2mm, and distance of the sample initial surface away from flame-thrower nozzle is 10 ± 0.2mm, flame ablation angle
It is 90 °.Specific oxy-acetylene flame burns candle experiment parameter：O2Flow 1512L/h, C2H2Flow 1116L/h, O2Atmospheric pressure 0.4Mpa,
C2H2Atmospheric pressure 0.095Mpa.
After tested, the prepared C/C composite materials ceramic matrix of resistance to ablation layer is in 3000 DEG C or so oxy-acetylene flame ablations
Between be increased to 80s and coating is not fallen off, therefore there is C/C composite materials 80s to stablize resistance to ablation ability.
Integrated embodiment 1, embodiment 2, embodiment 3 are understood：Reaction infiltration prepared by embodiment 1 is modified C/C composite woods
Expect the matrix of resistance to ablation 3000 DEG C or so oxy-acetylene flame ablation times up to：150s, and matrix does not have apparent ablation to be broken
Crackle.Therefore embodiment 1 is the preferred forms of the present invention.
The embodiment of the present invention only introduces its specific implementation mode, does not lie in and limits its protection domain.The skill of the industry
Art personnel can make certain modifications under the inspiration of the present embodiment, therefore all equivalence changes done according to the scope of the claims of the present invention
Or modification, it belongs in scope of the patent claims of the present invention.
Claims (3)
1. a kind of composite modified basis material of charcoal/charcoal, it is characterised in that：Including Carbon fibe layer (1), pyrolysis layer of charcoal (2), SiC layer
(3) and ZrC layers (4), wherein above-mentioned pyrolysis layer of charcoal (2) is covered in the surface of Carbon fibe layer (1), and SiC layer (3) is covered in pyrolysis
Layer of charcoal (2) surface, ZrC layers (4) are covered in SiC layer (3) surface；Above-mentioned pyrolysis layer of charcoal (2) alleviates Carbon fibe (1) and SiC layer (3)
Between thermal stress, SiC layer (3) alleviates thermal stress between pyrolysis layer of charcoal (2) and ZrC layers (4), makes pyrolysis layer of charcoal (2), SiC layer
(3) it is not fallen off in ablation environment with ZrC layers (4)；Above-mentioned pyrolysis layer of charcoal (2), SiC layer (3) and ZrC layers (4) include element：
Zr, Si and C, and mass percentage composition is：80~95%Zr powder, 5~20%Si powder and 0~5%C powder.
2. a kind of preparation process of the composite modified basis material of charcoal/charcoal as described in claim 1, which is characterized in that including with
Lower processing step：
(a) preparation of infiltrant：Weigh 80~95%Zr powder, 5~20%Si powder and 0~5%C powder respectively by mass fraction, then
Infiltrant is made using 1~3h of rotating speed 200~250r/min ball millings；
(b) preparation of Carbon fibe/pyrolytic carbon/SiC/ZrC composite materials：C/C matrixes are completely covered in infiltrant in step (a)
After be put into graphite crucible, then graphite crucible is put into vacuum drying oven, be passed through flow be 500~600ml/min protectiveness
Furnace temperature is risen to 1800~2000 DEG C with the heating rate of 7.5~12.5 DEG C/min, 1~3h is kept the temperature, then with 7~10 by gas
DEG C/furnace temperature is down to 1000~1200 DEG C by the cooling rate of min, it closes power supply and is naturally cooling to room temperature, in C/C basis materials
Portion forms the anti-yaw damper carbon carbon composite with Carbon fibe/pyrolytic carbon/SiC/ZrC gradient-structures；
(c) Carbon fibe/pyrolytic carbon/SiC/ZrC composite inner structural stresses are alleviated：The charcoal that will be prepared in step (b)
Fiber/pyrolytic carbon/SiC/ZrC composite materials are put into high temperature furnace, and furnace temperature is risen to 1500 with the heating rate of 7~10 DEG C/min
~1800 DEG C, 1~3h is kept the temperature, closing power supply with furnace cooling is naturally cooling to room temperature, obtains sample；
(d) oxy-acetylene flame ablation instrument is used to carry out ablation property test：Sample in step c is positioned over equipped with cooling system
Objective table on, use ablation rifle nozzle diameter for 2mm, distance of the sample initial surface away from flame-thrower nozzle be 9.8~10.2mm,
Flame ablation angle is 90 ° of progress ablation property tests.
3. a kind of preparation process of composite modified basis material of charcoal/charcoal according to claim 2, it is characterised in that：It is described
Step d in specific oxy-acetylene flame burn candle experiment parameter and be：O2Flow 1512L/h, C2H2Flow 1116L/h, O2Atmospheric pressure
0.4Mpa, C2H2Atmospheric pressure 0.095Mpa.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109910390A (en) * | 2019-03-04 | 2019-06-21 | 湖北菲利华石英玻璃股份有限公司 | A kind of prefabricated preparation of Graded Density resin composite materials |
| CN110885257A (en) * | 2019-12-11 | 2020-03-17 | 中国人民解放军空军工程大学 | Carbon/carbon composite material surface functional coating and preparation method thereof |
| CN112608168A (en) * | 2020-12-18 | 2021-04-06 | 江西信达航科新材料科技有限公司 | High-temperature-resistant and oxidation-resistant ceramic coating and preparation method thereof |
| CN114455966A (en) * | 2022-01-22 | 2022-05-10 | 巩义市泛锐熠辉复合材料有限公司 | High-temperature-resistant fastener and preparation method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105461357A (en) * | 2015-11-18 | 2016-04-06 | 中南大学 | A charcoal/charcoal composite material ablation-resisting coating and a preparing process thereof |
-
2018
- 2018-06-12 CN CN201810601977.7A patent/CN108794039A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105461357A (en) * | 2015-11-18 | 2016-04-06 | 中南大学 | A charcoal/charcoal composite material ablation-resisting coating and a preparing process thereof |
Non-Patent Citations (2)
| Title |
|---|
| ZHE ZHOU ET AL.: "Microstructure and ablation performance of SiC–ZrC coated C/C composites prepared by reactive melt infiltration", 《CERAMICS INTERNATIONAL》 * |
| 汪沅 等: "C/C 复合材料表面反应熔渗法制备SiC-ZrC涂层的组织与结构", 《粉末冶金材料科学与工程》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109910390A (en) * | 2019-03-04 | 2019-06-21 | 湖北菲利华石英玻璃股份有限公司 | A kind of prefabricated preparation of Graded Density resin composite materials |
| CN110885257A (en) * | 2019-12-11 | 2020-03-17 | 中国人民解放军空军工程大学 | Carbon/carbon composite material surface functional coating and preparation method thereof |
| CN110885257B (en) * | 2019-12-11 | 2022-02-15 | 中国人民解放军空军工程大学 | Carbon/carbon composite material surface functional coating and preparation method thereof |
| CN112608168A (en) * | 2020-12-18 | 2021-04-06 | 江西信达航科新材料科技有限公司 | High-temperature-resistant and oxidation-resistant ceramic coating and preparation method thereof |
| CN112608168B (en) * | 2020-12-18 | 2022-08-09 | 江西信达航科新材料科技有限公司 | High-temperature-resistant and oxidation-resistant ceramic coating and preparation method thereof |
| CN114455966A (en) * | 2022-01-22 | 2022-05-10 | 巩义市泛锐熠辉复合材料有限公司 | High-temperature-resistant fastener and preparation method thereof |
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