CN1793037A - Carbon/ceramic heat-resistant composite material and preparation process thereof - Google Patents
Carbon/ceramic heat-resistant composite material and preparation process thereof Download PDFInfo
- Publication number
- CN1793037A CN1793037A CN 200510047738 CN200510047738A CN1793037A CN 1793037 A CN1793037 A CN 1793037A CN 200510047738 CN200510047738 CN 200510047738 CN 200510047738 A CN200510047738 A CN 200510047738A CN 1793037 A CN1793037 A CN 1793037A
- Authority
- CN
- China
- Prior art keywords
- carbon
- sic
- resistant composite
- composite material
- ceramic heat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Ceramic Products (AREA)
Abstract
The invention relates to a carbon/ceramic heat proof compounding material and the manufacturing method. The wt% of the material is C squama 25-65, ceramic powder SiC+B<SUB>4</SUB>C 30-60, of which SiC: SiC+B<SUB>4</SUB>C=5:1, TiO<SUB>2</SUB> 5-13, adopting acetone phenolic resin as binding agent. Mixing the constituents, molding at the pressure of 30-50MPa, keeping the temperature and cooling to room temperature, the material would be gained. The invention has the feature of light, high intensity, high toughness, antifriction, high temperature poof, and anti-oxidation.
Description
Technical field
The present invention relates to a kind of heat-resistant composite material and preparation method, be specifically related to a kind of carbon/ceramic heat-resistant composite material and preparation method thereof, more properly say to relate to a kind of C-SiC-B
4C-TiB
2Heat-resistant composite material and preparation method thereof.
Background technology
Density is little, high temperature resistant, heat-shock resistance is good owing to having for carbon material, intensity does not raise the degradation characteristics with temperature, can be used as heat insulation material.But the carbon material at high temperature is easy to oxidation, is limiting range of application.Present heat insulation material mainly adopts the C/C matrix material, for the oxidation-resistance that improves material and anti-ablative, usually in material surface coated with high temperature oxidation resistant coating, to realize the protection to heat insulation material.Heat insulation material often will stand a plurality of thermal cyclings and surface damage, and this just requires material to have whole oxidation resistant performance and has the function of self-protection.
Find by literature search, Hu Xiaokai, week the sound strive forward, people such as summer golden child are at " University Of Xiangtan's journal " (natural science edition) 2003,25 (1): P39-P42 writes articles " binder free C-SiC-B
4The research of the preparation of C carbon/ceramic composite material and high-temperature oxidation resistance ", this article general description C-SiC-B
4The preparation of C carbon/ceramic composite material and oxidation characteristic thereof.Illustrate that this heat-resistant composite material can have stronger high-temperature oxidation resistance and self-healing.
But, utilize 400 purpose SiC and 500 purpose B owing to adopt raw petroleum coke to do carbon source
4C is that ceramic raw material is at 1600 ℃ of preparation carbon/ceramic composite materials, in the raw material raw petroleum coke fugitive constituent how much determined the material sintering time viscosifying power, green coke comprise bonding sintering under the low temperature and the solid state sintering under the high temperature from sintering process, the granular graphite crystallization degree that its sintering process complexity and green coke generate is not high, so the material oxidation resistance temperature of this method preparation is lower, influenced the use range of this advanced composite material.
Summary of the invention
The objective of the invention is to develop a kind of C-SiC-B of containing in order to overcome the defective that prior art exists
4C-TiB
2Carbon/ceramic heat-resistant composite material and preparation method thereof, select for use the C scale as carbon source matrix, TiO
2As sintering aid,, when making the resistance of oxidation increase of this matrix material, improve tension, bending strength and the toughness of pottery in conjunction with the preparation technology who is fit to matrix material of the present invention.Make its surperficial lagging material that is mainly used in 1600～1800 ℃ of 650～1260 ℃ of warm areas in the space flight carrier heat-protection system and high-temperature zones, and reach maximum range and satisfy of the requirement of other each association area heat insulation material.
Carbon/ceramic heat-resistant composite material of the present invention is formed and is comprised C, SiC, B
4C and TiO
2, its main points are weight percent proportionings of matrix material: the C scale is 25～65% as the carbon source matrix, ceramics powder SiC+B
4C is 30～60%, wherein SiC: B
4C=5: 1, TiO
2Be 5～13%, adopt acetone resol to make binding agent, add-on is 6～14% of a material gross weight.
Above-mentioned raw materials C scale median size is 50～400 μ m, and the SiC median size is less than 1 μ m, B
4The C median size is less than 3 μ m, TiO
2Median size is 1 μ m.
The binding agent acetone resol carbon content that is adopted is 20%.
The preparation method of carbon/ceramic heat-resistant composite material of the present invention, its raw material includes C, SiC, B
4C and TiO
2, its main points are to be undertaken by following processing condition and step:
1) former material assembly:
With weight proportion, choosing the C scale is 25～65% as the carbon source matrix, ceramics powder SiC+B
4C is 30～60%, wherein SiC: B
4C=5: 1, TiO
2Be 5～13%;
2) raw material mixes: above-mentioned confected materials is placed mixing tank, and as binding agent, add-on is 6～14% of a material gross weight, under agitation condition, raw material is mixed with acetone resol;
3) shaped by fluid pressure: mixed raw materials is put into mould, compression molding under 15～25MPa pressure;
4) hot pressed sintering: the base substrate after the mold pressing is put into hot pressing furnace together with mould,, begin to heat up during less than 10Pa in vacuum tightness, heat-up rate is 10～20 ℃/minute, when temperature reaches 1400 ℃～1500 ℃, is incubated 30～60 minutes; Afterwards, vacuum tightness less than the 10Pa condition under or under argon atmospher, continue to heat up, the argon atmospher pressure-controlling is 0.07～0.13MPa in the stove, temperature rise rate is 10～30 ℃/minute, when being heated to 1950～2100 ℃ of hot pressed sintering temperature, insulation, and carry out hot pressing, hot pressing pressure is 30～50MPa pressure, and the hot pressing soaking time is 60～240 minutes; Afterwards, naturally cool to room temperature, lay down pressure, obtain carbon/ceramic heat-resistant composite material.
Above-mentioned raw materials C scale median size is 50～400 μ m, and the SiC median size is less than 1 μ m, B
4The C median size is less than 3 μ m, TiO
2Median size is 1 μ m; Selected binding agent acetone resol carbon content is 20%.
In blender to the mixed preparing of raw material be guarantee to stir and the not broken again situation of C scale under carry out, take the intermittent type stirring so stir, per 30 seconds circulation primary stirred 20 minutes altogether, the stirrer rotating speed is 200 rev/mins; More even for raw material is mixed, earlier with SiC, B
4C and TiO
2These three kinds of ceramic powder carry out ball milling to be mixed, and ball-milling medium is analytical pure acetone or raw spirit, and abrading-ball is alumina balls, ball milling is 6～24 hours, after the powder mix oven dry, press the above-mentioned raw materials preparation steps with C scale raw material again, under the mechanical stirring condition, mix.
Above-mentioned mixed raw materials is to put into the high-strength graphite mould, utilizes hydropress to produce pressure with the compound compression molding.
The present invention compared with the prior art has tangible advantage and positively effect:
1, the present invention has adopted the C scale to replace raw petroleum coke to do carbon source, because the C scale is through the natural formation of High Temperature High Pressure, have advantages of higher stability and oxidation-resistance, and utilize the graphite scale to be difficult to form the feature of chemical bond with body material, and the inner inherent of C scale becomes layer defects (Mrozowski slit), matrix material can have very low Young's modulus, its breaking strain is far above oxide refractories, thereby can bear quite high rupture stress, and have high thermal conductivity advantage with graphite itself and combine, finally make the anti-thermal shock factor R of the carbon/ceramic composite material that contains the C scale
AtGreatly;
2, fracture toughness property and the bending strength in order to strengthen its ceramic phase, the present invention introduces TiO when reaction
2, solid state sintering generates TiB
2The second phase particle toughening, thus make product have lightweight, high strength, toughness is big, high temperature resistant, anti-thermal shock, advantage such as anti-oxidant;
3, C-SiC-B of the present invention
4C-TiB
2Matrix material, in the time of in being exposed to high temperature oxidation stability atmosphere, the carbon on surface is at first oxidized, forms by B
4The granular layer that C and SiC form, the SiC in the granular layer, B
4C is simultaneously constantly oxidized, can consume in hole the oxygen to the material internal diffusion on the one hand, the rate of oxidation of slowing down carbon base body, the more important thing is can produce good fluidity or B
2O
3SiO
2Liquid phase, self-protection and whole oxidation resistant function are played in the surface of part or totally-enclosed material.So C-SiC-B
4C-TiB
2Matrix material has the performance more excellent than single-component material.It is that carbon material and stupalith are combined plain and this two classes material property complementary advantage of pottery of performance charcoal, prepare the physical strength height, high temperature resistant, corrosion-resistant, wearability is good, anti-oxidant, anti-slag, anti-thermal shock ability are strong, and possess the novel high-performance engineering materials of good conductive thermal conductivity, machinable and self-lubricating ability.This product is mainly as 650～1260 ℃ of warm areas in the space flight carrier heat-protection system and 1600～1800 ℃ of surperficial lagging materials in high-temperature zone and other more extensive association area.
Embodiment
Example 1: the C scale of choosing median size and be 60 μ m is as the carbon source matrix, and choosing SiC, the median size that median size is 0.5 μ m is the B of 1.5 μ m
4C and median size are the TiO of 1 μ m
2Be the ceramic phase raw material.At first with 25%SiC, 5%B
4C and 6%TiO
2Carrying out ball milling mixes, ball-milling medium is an analytical pure acetone, abrading-ball is alumina balls, ball milling 12 hours, after the powder mix oven dry, above-mentioned powder mix and 64%C scale are placed agitator, and the acetone resol that adds total material 7% stirs as wedding agent, rotating speed is 200 rev/mins, stirs 20 minutes.Mixed raw materials is put into graphite jig at room temperature, utilize hydropress to produce 25MPa pressure, compression molding.Biscuit is put into vacuum sintering furnace together with mould,, be warming up to 1400 ℃, be incubated 30 fens with 20 ℃/minute speed when vacuum tightness during less than 10Pa; Continue heating with 30 ℃/minute temperature rise rate in vacuum tightness under less than the 10Pa condition, insulation when sintering temperature is 1950 ℃, and mould applied 30MPa pressure, hot pressed sintering is 60 minutes under the condition of heat-insulation pressure keeping; Power failure is lowered the temperature naturally and is cooled to room temperature, lays down pressure, prepares C-SiC-B
4C-TiB
2Heat-resistant composite material.Add TiO
2C-SiC-B
4The folding strength of C matrix material reaches 220MPa, than not adding TiO
2C-SiC-B
4The C matrix material exceeds 4 times, thermal-shock resistance Δ T=953K.700 ℃ of-1300 ℃ of tests of at each temperature matrix material having been carried out high-temperature oxidation resistance.The result shows: matrix material surface when 1100 ℃, 1200 ℃ oxidations can generate solid-state self-healing anti-oxidation protective membrane, and it is oxidized that the generation of this layer protective membrane can stop matrix material to continue; And the self-healing protective membrane that generates during 1300 ℃ of following oxidations when matrix material is in a liquid state, this moment matrix material the antioxidant property variation.700 ℃ of air atmosphere oxidations 30 minutes, oxidation weight loss accounts for gross weight 4%.
Example 2: the C scale of choosing median size and be 400 μ m is as the carbon source matrix, and choosing SiC, the median size that median size is 0.5 μ m is the B of 1.5 μ m
4C and median size are the TiO of 1 μ m
2Be the ceramic phase raw material.At first with 35%SiC, 7%B
4C and 9%TiO
2Carrying out ball milling mixes, ball-milling medium is a raw spirit, abrading-ball is alumina balls, ball milling 12 hours, after the powder mix oven dry, above-mentioned powder mix and 49%C scale are placed agitator, and the acetone resol that adds total material 10% stirs as wedding agent, rotating speed is 200 rev/mins, stirs 20 minutes.Mixed raw materials is put into graphite jig at room temperature, utilize hydropress to produce 25MPa pressure, compression molding.Biscuit is put into vacuum sintering furnace together with mould,, be warming up to 1450 ℃, be incubated 45 fens with 15 ℃/minute speed when vacuum tightness during less than 10Pa; Charge into the argon gas of 0.08MPa, with 20 ℃/minute temperature rise rate heating, be incubated when sintering temperature is 2050 ℃, and mould is applied 40MPa pressure afterwards, hot pressed sintering is 150 minutes under the condition of heat-insulation pressure keeping; Power failure is lowered the temperature naturally and is cooled to room temperature, lays down pressure, prepares C-SiC-B
4C-TiB
2Matrix material.C-SiC-B
4The folding strength of C matrix material can reach 350MPa, thermal-shock resistance Δ T=1000K.700 ℃ of-1300 ℃ of tests of at each temperature matrix material having been carried out high-temperature oxidation resistance.The result shows: matrix material surface when 1100 ℃, 1300 ℃ oxidations can generate solid-state self-healing anti-oxidation protective membrane, and it is oxidized that the generation of this layer protective membrane can stop matrix material to continue.Ablate with laser analog, obtaining its linear ablative rate is 0.135mm/s.700 ℃ of air atmosphere oxidations 30 minutes, oxidation weight loss accounted for gross weight 1%.
Example 3: the C scale of choosing median size and be 200 μ m is as the carbon source matrix, and choosing SiC, the median size that median size is 0.5 μ m is the B of 1.5 μ m
4C and median size are the TiO of 1 μ m
2Be the ceramic phase raw material.At first with 50%SiC, 10%B
4C and 12%TiO
2Carrying out ball milling mixes, ball-milling medium is an analytical pure acetone, abrading-ball is alumina balls, ball milling 12 hours, after the powder mix oven dry, above-mentioned powder mix and 28%C scale are placed agitator, and the acetone resol that adds total material 13% stirs as wedding agent, rotating speed is 200 rev/mins, stirs 20 minutes.Mixed raw materials is put into graphite jig at room temperature, utilize hydropress to produce 25MPa pressure, compression molding.Biscuit is put into vacuum sintering furnace together with mould, and vacuum tightness is warming up to 1500 ℃ with 10 ℃/minute speed during less than 10Pa, is incubated 60 fens; Pour the argon gas of 0.12MPa; With 10 ℃/minute temperature rise rate heating, be incubated when sintering temperature is 2100 ℃, and mould is applied 50MPa pressure afterwards, hot pressed sintering is 240 minutes under the condition of heat-insulation pressure keeping; Power failure is lowered the temperature naturally and is cooled to room temperature, lays down pressure, prepares C-SiC-B
4C-TiB
2Matrix material.C-SiC-B
4The folding strength of C matrix material can reach 520MPa, thermal-shock resistance Δ T=1000K.700 ℃ of-1400 ℃ of tests of at each temperature matrix material having been carried out high-temperature oxidation resistance.The result shows: matrix material surface when 1100 ℃, 1400 ℃ oxidations can generate solid-state self-healing anti-oxidation protective membrane, and it is oxidized that the generation of this layer protective membrane can stop matrix material to continue.Ablate with laser analog, obtaining its linear ablative rate is 0.08mm/s.700 ℃ of air atmosphere oxidations 30 minutes, oxidation weight loss accounted for gross weight 0.5%.
Claims (9)
1, a kind of carbon/ceramic heat-resistant composite material is formed and is comprised C, SiC, B
4C and TiO
2, it is characterized in that the weight percent proportioning of matrix material: the C scale is 25～65% as the carbon source matrix, ceramics powder SiC+B
4C is 30～60%, wherein SiC: B
4C=5: 1, TiO
2Be 5～13%, adopt acetone resol to make binding agent, add-on is 6～14% of a material gross weight.
2, according to the described a kind of carbon/ceramic heat-resistant composite material of claim 1, it is characterized in that: raw material C scale median size is 50～400 μ m, and the SiC median size is less than 1 μ m, B
4The C median size is less than 3 μ m, TiO
2Median size is 1 μ m.
3,, it is characterized in that binding agent acetone resol carbon content is 20% according to the described a kind of carbon/ceramic heat-resistant composite material of claim 1.
4, according to the preparation method of the described a kind of carbon/ceramic heat-resistant composite material of claim 1, raw material is formed and is comprised C, SiC, B
4C and TiO
2, it is characterized in that being undertaken by following processing condition and step:
1) former material assembly: is 25～65% with weight proportion C scale as the carbon source matrix, and ceramics powder is SiC+B
4C is 30～60%, wherein SiC: B
4C=5: 1, TiO
2Be 5～13%;
2) raw material mixes: above-mentioned confected materials is placed mixing tank, and as binding agent, add-on is 6～14% of a material gross weight, under agitation condition, raw material is mixed with acetone resol;
3) shaped by fluid pressure: above-mentioned mixed raw materials is put into mould, compression molding under 15～25MPa pressure;
4) hot pressed sintering: the base substrate after the above-mentioned mold pressing is put into hot pressing furnace together with mould,, begin to heat up during less than 10Pa in vacuum tightness, heat-up rate is 10～20 ℃/minute, when temperature reaches 1400 ℃～1500 ℃, is incubated 30～60 minutes; Afterwards, vacuum tightness less than the 10Pa condition under or under argon atmospher, continue to heat up, the argon atmospher pressure-controlling is 0.07～0.13MPa in the stove, temperature rise rate is 10～30 ℃/minute, when being heated to 1950～2100 ℃ of hot pressed sintering temperature, hot pressing is carried out in insulation, hot pressing pressure is 30～50MPa pressure, and the hot pressing soaking time is 60～240 minutes; Afterwards, naturally cool to room temperature, lay down pressure, finally obtain carbon/ceramic heat-resistant composite material.
5, according to the preparation method of the described a kind of carbon/ceramic heat-resistant composite material of claim 4, it is characterized in that: raw material C scale median size is 50～400 μ m, and the SiC median size is less than 1 μ m, B
4The C median size is less than 3 μ m, TiO
2Median size is 1 μ m.
6, according to the preparation method of the described a kind of carbon/ceramic heat-resistant composite material of claim 4, it is characterized in that: the binding agent acetone resol carbon content that is adopted in the preparation of raw material is 20%.
7, according to the preparation method of the described a kind of carbon/ceramic heat-resistant composite material of claim 4, it is characterized in that: in mixing tank,, be earlier SiC, B to the mixing of raw material
4C and TiO
2Three kinds of ceramic powder carry out ball milling to be mixed, and ball-milling medium is analytical pure acetone or raw spirit, and abrading-ball is alumina balls, and ball milling 6～24 hours after the powder mix oven dry, with C scale raw material, mixes under mechanical stirring again.
8, according to the preparation method of claim 4 or 7 described a kind of carbon/ceramic heat-resistant composite materials, it is characterized in that: in mixing tank, the mixed preparing of raw material, take intermittent type to stir, per 30 seconds circulation primary stirred 20 minutes altogether, and the stirrer rotating speed is 200 rev/mins.
9, according to the preparation method of the described a kind of carbon/ceramic heat-resistant composite material of claim 4, it is characterized in that: mixed raw materials is to put into the high-strength graphite mould, utilizes hydropress to produce pressure with the compound compression molding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005100477384A CN100337982C (en) | 2005-11-18 | 2005-11-18 | Carbon/ceramic heat-resistant composite material and preparation process thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005100477384A CN100337982C (en) | 2005-11-18 | 2005-11-18 | Carbon/ceramic heat-resistant composite material and preparation process thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1793037A true CN1793037A (en) | 2006-06-28 |
| CN100337982C CN100337982C (en) | 2007-09-19 |
Family
ID=36804702
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2005100477384A Expired - Fee Related CN100337982C (en) | 2005-11-18 | 2005-11-18 | Carbon/ceramic heat-resistant composite material and preparation process thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100337982C (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101555140B (en) * | 2009-05-22 | 2011-10-26 | 东北大学 | Loose sintering preparation method of titanium diboride compact complex material |
| CN104878393A (en) * | 2015-05-22 | 2015-09-02 | 苏州市贝克生物科技有限公司 | Cultural relics surface oxidation resistant coating and preparation method of cultural relics surface oxidation resistant coating |
| CN105111931A (en) * | 2015-08-31 | 2015-12-02 | 中国人民解放军国防科学技术大学 | Strong-laser-ablation-resistant protective coating and preparation method thereof |
| CN108725409A (en) * | 2017-04-20 | 2018-11-02 | 美国联合金属制品股份有限公司 | Height friction heat insulator |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4067743A (en) * | 1976-09-02 | 1978-01-10 | Boris Georgievich Arabei | Heat-absorbing material |
| CN1086800A (en) * | 1993-11-16 | 1994-05-18 | 中国建筑材料科学研究院 | Ceramic heat insulation material and technology of preparing thereof |
| RU2101262C1 (en) * | 1996-02-21 | 1998-01-10 | Аркадий Станиславович Кондаков | Tough ceramic material |
-
2005
- 2005-11-18 CN CNB2005100477384A patent/CN100337982C/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101555140B (en) * | 2009-05-22 | 2011-10-26 | 东北大学 | Loose sintering preparation method of titanium diboride compact complex material |
| CN104878393A (en) * | 2015-05-22 | 2015-09-02 | 苏州市贝克生物科技有限公司 | Cultural relics surface oxidation resistant coating and preparation method of cultural relics surface oxidation resistant coating |
| CN105111931A (en) * | 2015-08-31 | 2015-12-02 | 中国人民解放军国防科学技术大学 | Strong-laser-ablation-resistant protective coating and preparation method thereof |
| CN105111931B (en) * | 2015-08-31 | 2017-10-03 | 中国人民解放军国防科学技术大学 | Protective coating of anti-light laser ablation and preparation method thereof |
| CN108725409A (en) * | 2017-04-20 | 2018-11-02 | 美国联合金属制品股份有限公司 | Height friction heat insulator |
| US10724592B2 (en) | 2017-04-20 | 2020-07-28 | Consolidated Metco, Inc. | High friction insulator |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100337982C (en) | 2007-09-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100503513C (en) | SiC-BN-C composite material and preparation method thereof | |
| CN101456737B (en) | Boron carbide base composite ceramic and preparation method thereof | |
| WO2020042950A1 (en) | Short-fiber-reinforced oriented max-phase ceramic-based composite and preparation method therefor | |
| CN112679233B (en) | Preparation method of silicon carbide coating for carbon-carbon composite material | |
| CN109400164B (en) | MAX phase/nitride ceramic layered gradient composite material and rapid preparation method and application thereof | |
| CN100432016C (en) | Method of manufacturing aluminium nitride/boron nitride multiple phase ceramic | |
| CN111004953B (en) | Molten aluminum corrosion resistant cermet material and preparation method and application thereof | |
| CN108863396B (en) | Silicon nitride-based continuous functional gradient ceramic ball and preparation method and application thereof | |
| Wang et al. | Effect of the evolution of phenol–formaldehyde resin on the high-temperature bonding | |
| CN111848172B (en) | Molybdenum disilicide/silicon carbide three-dimensional polymer precursor ceramic and preparation method thereof | |
| CN111018540A (en) | High-strength boron nitride ceramic composite material based on low-temperature hot-pressing sintering | |
| CN111085688A (en) | Tungsten/silicon nitride/tungsten symmetrical layered gradient composite material and rapid preparation method and application thereof | |
| CN100337982C (en) | Carbon/ceramic heat-resistant composite material and preparation process thereof | |
| He et al. | Preparation of fully stabilized cubic-leucite composite through heat-treating Cs-substituted K-geopolymer composite at high temperatures | |
| CN106904977A (en) | A kind of method that two-step sintering method prepares the tough Si3N4 ceramic materials of table hard-core | |
| CN111716494A (en) | Method for preparing layered complex phase ceramic by using reaction sintering method | |
| CN104310976A (en) | Highly wear-resistant high-temperature ceramic | |
| Feng et al. | Vibration assisted hot‐press sintering of AlN ceramics | |
| CN107746282B (en) | In-situ silicon carbide fiber reinforced liquid phase sintered silicon carbide ceramic and manufacturing method thereof | |
| CN104628392A (en) | Preparation method of compact aluminum nitride-boron nitride composite material | |
| CN101798222A (en) | Al2O3-Ni-C-B4C composite ceramic and preparation method thereof | |
| CN110698207A (en) | Silicon nitride-based layered ceramic composite material and preparation method thereof | |
| CN117658641A (en) | Method for preparing high-density SiC ceramic based on selective laser 3D printing and two-step sintering | |
| CN109734452B (en) | Pressureless sintering preparation of high-density Ti2Method for preparing AlN ceramic | |
| CN110436896B (en) | Method for preparing high-strength and high-toughness ceramic material by thermally cracking silica gel and inorganic filler compound |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |