CN103044054A - Zirconium-titanium carbide-modified anti-ablative carbon/carbon composite material and preparation method thereof - Google Patents
Zirconium-titanium carbide-modified anti-ablative carbon/carbon composite material and preparation method thereof Download PDFInfo
- Publication number
- CN103044054A CN103044054A CN2012105323908A CN201210532390A CN103044054A CN 103044054 A CN103044054 A CN 103044054A CN 2012105323908 A CN2012105323908 A CN 2012105323908A CN 201210532390 A CN201210532390 A CN 201210532390A CN 103044054 A CN103044054 A CN 103044054A
- Authority
- CN
- China
- Prior art keywords
- carbon
- zirconium
- carbon composite
- preparation
- temperature
- 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.)
- Pending
Links
Images
Landscapes
- Carbon And Carbon Compounds (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
Abstract
The invention discloses a zirconium-titanium carbide-modified anti-ablative carbon/carbon composite material and a preparation method thereof. The preparation method comprises the following steps: (1) performing high-temperature heat treatment on a carbon fiber preform, and placing into a chemical gas-phase permeation furnace for depositing a certain amount of pyrolytic carbon to prepare low-density carbon/carbon composite material; and (2) placing the carbon/carbon composite material with the permeated pyrolytic carbon on zirconium-titanium alloy powder, and preparing the modified carbon/carbon composite material containing a zirconium-titanium carbide through a high-temperature infiltration reaction method. The process method disclosed by the invention is simple and convenient to operate, and can be used for preparing a special-shaped part with large size or complex structure; and the zirconium-titanium carbide-modified anti-ablative carbon/carbon composite material is suitable for basic modification of the anti-ablative carbon/carbon composite materials in heat-resistant parts of aerospace crafts.
Description
Technical field
The present invention relates to anti-ablation carbon/carbon composite of a kind of zirconium titanium carbide modification and preparation method thereof.
Background technology
Carbon/carbon composite is the new type high temperature material of carbon fiber reinforced carbon matrix body, and this material light specific gravity, theoretical density are 2.2g/cm
3Have high-strength modulus, little, the anti-ablation of thermal expansivity, antifatigue, unreactiveness, dimensional stability height, particularly the intensity temperature raises and the series of advantages such as rising and high-fracture toughness, low creep under the high temperature, be desirable thermal structure and ablation resistant material, be widely used in aerospace field.At present, countries in the world all will resist the ablation carbon/carbon composite as the preferred material of nose cone and the leading edge of space shuttle.Carbon/carbon composite has the heat-resisting characteristics of light weight, thereby also is the important equivalent material of the hot-end component alloy material of hypersonic vehicle.
But easily oxidized when carbon/carbon composite uses in the high temperature aerobic environment.Under aerobic conditions, the initial oxidation temperature of carbon/carbon composite is 370 ℃; When being higher than 500 ℃, the rapid oxidation of carbon/carbon composite meeting, and catastrophic explosion occurs.And high Mach aircraft (〉 5Ma) the temperature of nose cone, the edge of a wing and combustion chamber tend to reach 2000-2800 ℃ high temperature, these heating parts also will stand washing away of long high temperature and high speed oxidative airstream and particle simultaneously.And pure carbon/carbon composite also is difficult to competent so harsh applied environment.Therefore, research is carried out matrix modification to carbon/carbon composite, further improves the Burning corrosion resistance energy of carbon/carbon composite, can be applied on the parts of anti-ablation of hypersonic vehicle to have great significance.
The ceramic phase of introducing the anti-ablation of high-melting-point in matrix of carbon/carbon composite materials is the effective measure of Burning corrosion resistance energy that improves carbon/carbon composite.In these potteries, zirconium carbide because of have very high fusing point (3540 ℃) with and corresponding zirconium white also has high-melting-point (2500 ℃) and the low advantages such as diffusion coefficient usually are selected as anti-ablator.With respect to other high-melting-point carbide such as tantalum carbide, hafnium carbide, zirconium carbide has lower density and modulus, and cheaper preparation cost.But zirconium carbide also has weak point, and that is exactly when when low-temperature zone (＜2500 ℃), and the zirconium white that the zirconium carbide oxidation generates is a kind of structure of porosity and looseness, this to the anti-ablation of material and anti-oxidant be disadvantageous.Therefore, but introduced the slightly low carbide of very high its oxide compound fusing point of another fusing point---titanium carbide in this technique.The fusing point of titanium carbide is 3140 ℃, and its corresponding oxide compound fusing point is 1840 ℃, and titanium oxide has the diffusion coefficient lower than zirconium white.Both compound can form oxide film in oxidizing atmosphere, and then the erosion of opposing Sauerstoffatom and particle and provide protection for carbon matrix.This shows that introducing simultaneously two kinds of carbide can have very important effect to the Burning corrosion resistance that improves carbon/carbon composite.
Goal of the invention
Purpose of the present invention is exactly for the Burning corrosion resistance energy of further raising carbon/carbon composite at 2000 ℃ of-2800 ℃ of temperature sections, and a kind of brand-new anti-ablation carbon/carbon composite of zirconium titanium carbide modification and preparation method thereof is provided.
The objective of the invention is to realize by following manner:
The preparation method of the anti-ablation carbon/carbon composite of a kind of zirconium titanium carbide modification may further comprise the steps successively:
(1) with the carbon fabric perform high-temperature heat treatment;
(2) deposit RESEARCH OF PYROCARBON on the carbon fabric perform that step (1) was processed, obtain low-density carbon/carbon composite; (3) the low-density carbon/carbon composite that step (2) is obtained places on the zirtan powder and prepares the carbon/carbon composite that contains the zirconium titanium carbide by the reaction of high temperature infiltration.
The described high-temperature heat treatment of step (1) is to be 0.1-0.9g.cm with density
-3Carbon fabric perform place the pyrographite stove in 2000-2300 ℃ the insulation 1-3h.During high-temperature heat treatment, the temperature rise rate from the room temperature to 2000-2300 ℃ is 5-10 ℃/min, and soaking time is 1-3h, and rate of temperature fall is 5-8 ℃/min, when temperature is down to 1200 ℃, and furnace cooling.
The described carbon fabric perform of step (1) comprises the whole felt of carbon fiber acupuncture, and carbon fiber is carefully compiled the carbon fibre fabric of the multidimensional braiding such as puncture felt body or lamination acupuncture.
Adopt the chemical vapor infiltration deposition to obtain low-density carbon/carbon composite in the step (2).
Step (2) concrete steps are as follows: take hydrogen as carrier gas, propylene or methane are carbon-source gas, with the cvd furnace internal reaction deposition RESEARCH OF PYROCARBON of carbon fabric perform at high temperature.Temperature is 1000-1300 ℃ in the cvd furnace, and furnace pressure is 0.3-3.8Kpa, and the reaction times is 60-300h.
Step (3) concrete steps are as follows: at first take by weighing the zirtan powder, the 2-4 of consumption take preparing low-density carbon/carbon composite weight as benchmark doubly, alloy powder is placed the compacting of graphite tank, and after placing preparing low-density carbon/carbon composite on the alloy powder, the graphite tank is placed in the High Temperature Furnaces Heating Apparatus heat-treats; Treatment temp is 1900-2300 ℃, and soaking time is 0.5-2h, omnidistance argon shield.Temperature rise rate is 5-15 ℃/min during thermal treatment, and rate of temperature fall is 3-8 ℃/min, when being cooled to 600-900 ℃, and furnace cooling.
Described zirtan powder is prepared from by in the following dual mode any:
(1) zirconium ingot of purity 〉=99.9% and the ratio of titanium ingot take the Zr:Ti molecular ratio as 0.4-9 of purity 〉=99.9% are placed vacuum melting furnace, utilizing the standby alloy powder of aerosolization legal system behind the 1900-2300 ℃ of melting 1-3h under the argon shield condition, alloy powder is crossed 325 orders;
(2) with the zirconium powder of purity 〉=99.9% and the titanium valve of purity 〉=99.9%, the ball milling on high-energy planetary formula ball mill of the ratio take the Zr:Ti molecular ratio as 0.4-9 makes; Zirconium powder and titanium valve and the alloy powder that obtains are all crossed 325 mesh sieves; Rotational speed of ball-mill is 200-500r/min, and Ball-milling Time is 10h-25h, and ratio of grinding media to material is 4-10, and ball-milling medium is the argon shield dry grinding.。
The anti-ablation carbon/carbon composite of a kind of zirconium titanium carbide modification is the anti-ablation carbon/carbon composite of zirconium titanium carbide modification that is prepared from by above-mentioned method.
Advantage and the positively effect of invention
Compared with prior art, advantage of the present invention and positively effect are embodied in:
(1) technical process is few, and preparation cycle is short, and cost is low, can prepare large size or the special-shaped component of even structure;
(2) the pyrolytic carbon layer of chemical vapor infiltration preparation can be alleviated the thermal stresses of carbon fiber bundle and carbide ceramics phase preferably, also can stop preferably liquid zirtan to the erosion of carbon fiber, can also carbon source is provided mutually and then form the zirconium titanium carbide for zirtan;
(3) the anti-ablation carbon/carbon composite of the zirconium titanium carbide modification even structure of infiltration reaction preparation: carbon fiber is combined well with the ceramic phase interface with pyrolytic carbon and pyrolytic carbon, and ceramic phase distributes comparatively even; The zirconium titanium carbide has high-melting-point, and its oxide compound (2000-2800 ℃) in ablation process forms the moderate oxide film of viscosity, can provide better protecting for carbon matrix.
(4) it is even to have utilized the major advantage of above method to prepare basal body structure, have superior Burning corrosion resistance can the modification carbon/carbon composite, can satisfy the use of the structure unit of anti-ablation the in the lower long period of well-oxygenated environment.
Description of drawings
Fig. 1 is carbon fiber bundle in the matrix material for preparing of the present invention, RESEARCH OF PYROCARBON, zirconium titanium carbide at the i.e. three-dimensional thin micro Distribution pattern of compiling in the puncture felt body of a kind of carbon fabric perform;
Fig. 2 is carbon fiber bundle, RESEARCH OF PYROCARBON and zirconium titanium carbide three interface microscopic appearance in the matrix material for preparing of the present invention;
Fig. 3 is the composite material surface X ray diffracting spectrum that the present invention prepares: the H curve is the scanning result that embodiment 1 makes sample, and the L curve is the scanning result that embodiment 2 makes sample; Know that from figure it is by Zr that embodiment 1 makes sample
0.83Ti
0.17C
0.92, Ti
0.82Zr
0.18C
0.92Form with carbon, embodiment 2 makes sample then by Zr
0.57Ti
0.43C
1.01Form with carbon.
Fig. 4 is the macro morphology before and after the matrix material for preparing of the present invention is ablated: (a) preparing low-density carbon/carbon composite, (b) for the anti-ablation carbon/carbon composite of zirconium titanium carbide modification (c) embodiment 1 of the present invention preparation makes pattern behind 2000 ℃ of ablation 60s of sample, (d) embodiment 1 makes pattern behind 2500 ℃ of ablation 180s of sample; From scheming as seen; the fibre orientation of the preparing low-density carbon/carbon composite before the modification is comparatively obvious; it is comparatively fine and close that the surface of the matrix material after the modification seems; the sample that embodiment 1 makes is through behind the high temperature ablation; form obvious oxide white protective layer on the surface, this layer is conducive to a heatable brick bed ablation property of material.
Fig. 5 is that embodiment 1 makes sample at the change curve of 2500 ℃ of oxy-acetylene flame ablation propertys with the time of ablation.Material is along with the prolongation of the time of ablation, and its linear ablative rate and mass ablative rate rose before this slightly, then were obvious downward trend.
Embodiment
Be intended to further specify the present invention below in conjunction with embodiment, and unrestricted the present invention.
Embodiment 1
At first will be of a size of 180 * 180 * 20mm, density is 0.76g.cm
-3Carbon fiber is three-dimensional thin to be compiled puncture felt body (carbon fabric perform a kind of) and carries out high-temperature heat treatment with the organic gel of removing fiber surface and discharge stress.Treatment temp is 2300 ℃, and soaking time is 2h.Temperature rise rate is 10 ℃/min, and rate of temperature fall is 8 ℃/min, when being cooled to 1200 ℃, and furnace cooling.
Then carry out chemical vapor infiltration and carry out density to heat treated felt body, prepare low-density carbon/carbon composite.Take methane as carbon source, hydrogen deposits RESEARCH OF PYROCARBON at the felt body as carrier gas.Furnace pressure is 1.6Kpa, and the density of felt body carbon/carbon composite of gained behind 1100 ℃ of insulation 100h is 1.21-1.33g.cm
-3
After low-density carbon/carbon composite prepares, be cut to Φ 30 * 20 the right cylinder sample and with dehydrated alcohol to its cleaning, the oven dry with for subsequent use.
Next be preparation titanium-zirconium alloy powder.By zirconium powder (purity 〉=99.9%, 325 order sieves) and titanium valve (purity 〉=99.9%, 325 order sieves) take molecular ratio as 4:1(Zr:Ti) ratio ball milling on high-energy planetary formula ball mill make.Rotational speed of ball-mill is 450r/min, and Ball-milling Time is 25h, and ratio of grinding media to material is 8, and ball-milling medium is the argon shield dry grinding.Powder behind the ball milling goes out tank and packs with for subsequent use under argon shield, this process is finished in the vacuum that is full of argon gas is brought drill to an end case.
Then be to prepare the anti-ablation carbon/carbon composite of zirconium titanium carbide modification by the infiltration reaction method.The good mixed powder of weighing ball milling at first is with the 2.5 times weighings of powder amount with low-density carbon/carbon composite quality.Be placed in the graphite tank load weighted powder and compacting, the carbon/carbon composite that then will cut, clean and dry is placed on the powder mix of compacting.Then place High Temperature Furnaces Heating Apparatus to heat-treat in 2000 ℃ in the graphite tank.Soaking time is 3h, omnidistance argon shield.Temperature rise rate is 10 ℃/min, and rate of temperature fall is 8 ℃/min, when being cooled to 900 ℃, and furnace cooling.
Can get density by above technological process is 2.40-2.65g.cm
-3The anti-ablation carbon/carbon composite of carbide modification of the low titanium content of high zirconium.This matrix material can be superior at 2500 ℃ Burning corrosion resistance.Through 2500 ℃, the ablation of 60s oxy-acetylene flame, its linear ablative rate and mass ablative rate are respectively 0.002mm.s
-1And 2.30mg.s
-1, along with the 180s that extends to of the time of ablation, its linear ablative rate and mass ablative rate also descend to some extent, are respectively 0.001mm
-1And 1.6mg.s
-1
Embodiment 2
At first will be of a size of 180 * 180 * 20mm, density is 0.82g.cm
-3Carbon fiber is three-dimensional thin to be compiled puncture felt body (carbon fabric perform a kind of) and carries out high-temperature heat treatment with the organic gel of removing fiber surface and discharge stress.Treatment temp is 2300 ℃, and soaking time is 2h.Temperature rise rate is 10 ℃/min, and rate of temperature fall is 8 ℃/min, when being cooled to 1200 ℃, and furnace cooling.
Then carry out chemical vapor infiltration and carry out density to heat treated felt body, prepare low-density carbon/carbon composite.Take methane as carbon source, hydrogen deposits RESEARCH OF PYROCARBON at the felt body as carrier gas.Furnace pressure is 1.6Kpa, and the density of felt body carbon/carbon composite of gained behind 1100 ℃ of insulation 100h is 1.26-1.38g.cm
-3
After low-density carbon/carbon composite prepares, be cut to Φ 30 * 20 the right cylinder sample and with dehydrated alcohol to its cleaning, the oven dry with for subsequent use.
Next be preparation titanium-zirconium alloy powder.With zirconium ingot (purity 〉=99.9%) and titanium ingot (purity 〉=99.9%) take molecular ratio as 0.4:1(Zr:Ti) ratio place vacuum melting furnace; utilize the standby alloy powder of aerosolization legal system in argon shield behind 1900-2300 ℃ of melting 1-3h, alloy powder is all crossed 325 orders.
Then be to prepare the anti-ablation carbon/carbon composite of zirconium titanium carbide modification by the infiltration reaction method.Weighing powdered alloy at first is with the 2 times weighings of powder amount with low-density carbon/carbon composite quality.Be placed in the graphite tank load weighted powder and compacting, the carbon/carbon composite that then will cut, clean and dry is placed on the powder of compacting.Then place High Temperature Furnaces Heating Apparatus to heat-treat in 1850 ℃ in the graphite tank.Soaking time is 1h, omnidistance argon shield.Temperature rise rate is 10 ℃/min, and rate of temperature fall is 6 ℃/min, when being cooled to 900 ℃, and furnace cooling.
Can get density by above technological process is 2.30-2.60g.cm
-3The anti-ablation carbon/carbon composite of carbide modification of low zirconium high titanium content.This matrix material can be superior at 2000 ℃ Burning corrosion resistance.Through 2000 ℃, the ablation of 60s oxy-acetylene flame, its linear ablative rate and mass ablative rate are respectively 0.009mm.s
-1And 3.60mg.s
-1
Embodiment 3
At first will be of a size of 180 * 180 * 20mm, density is 0.42g.cm
-3The whole felt of carbon fiber acupuncture (carbon fabric perform a kind of) carries out high-temperature heat treatment with the organic gel of removing fiber surface and discharges stress.Treatment temp is 2300 ℃, and soaking time is 2h.Temperature rise rate is 10 ℃/min, and rate of temperature fall is 8 ℃/min, when being cooled to 1200 ℃, and furnace cooling.
Then carry out chemical vapor infiltration and carry out density to heat treated felt body, prepare low-density carbon/carbon composite.Take methane as carbon source, hydrogen deposits RESEARCH OF PYROCARBON at the felt body as carrier gas.Furnace pressure is 2.6Kpa, and the density of felt body carbon/carbon composite of gained behind 1100 ℃ of insulation 150h is 1.10-1.25g.cm
-3
After low-density carbon/carbon composite prepares, be cut to Φ 30 * 20 the right cylinder sample and with dehydrated alcohol to its cleaning, the oven dry with for subsequent use.
Next be preparation titanium-zirconium alloy powder.By zirconium powder (purity 〉=99.9%, 325 order sieves) and titanium valve (purity 〉=99.9%, 325 order sieves) take molecular ratio as 0.55:1(Zr:Ti) ratio ball milling on high-energy planetary formula ball mill make.Rotational speed of ball-mill is 450r/min, and Ball-milling Time is 25h, and ratio of grinding media to material is 10, and ball-milling medium is the argon shield dry grinding.Powder behind the ball milling goes out tank and packs with for subsequent use under argon shield, this process is finished in the vacuum that is full of argon gas is brought drill to an end case.
Then be to prepare the anti-ablation carbon/carbon composite of zirconium titanium carbide modification by the infiltration reaction method.The good mixed powder of weighing ball milling at first is with the 2 times weighings of powder amount with low-density carbon/carbon composite quality.Be placed in the graphite tank load weighted powder and compacting, the carbon/carbon composite that then will cut, clean and dry is placed on the powder mix of compacting.Then place High Temperature Furnaces Heating Apparatus to heat-treat in 1900 ℃ in the graphite tank.Soaking time is 1h, omnidistance argon shield.Temperature rise rate is 10 ℃/min, and rate of temperature fall is 6 ℃/min, when being cooled to 900 ℃, and furnace cooling.
Can get density by above technological process is 2.80-2.95g.cm
-3The anti-ablation carbon/carbon composite of carbide modification of low zirconium high titanium content.This matrix material can be superior at 2000 ℃ Burning corrosion resistance.Through 2000 ℃, the ablation of 60s oxy-acetylene flame, its linear ablative rate and mass ablative rate only are 0.003mm.s respectively
-1And 0.60mg.s
-1
Claims (10)
1. the preparation method of the anti-ablation carbon/carbon composite of zirconium titanium carbide modification is characterized in that: may further comprise the steps successively:
(1) with the carbon fabric perform high-temperature heat treatment;
(2) deposit RESEARCH OF PYROCARBON on the carbon fabric perform that step (1) was processed, obtain low-density carbon/carbon composite;
(3) the low-density carbon/carbon composite that step (2) is obtained places on the zirtan powder and prepares the carbon/carbon composite that contains the zirconium titanium carbide by the reaction of high temperature infiltration.
2. preparation method according to claim 1 is characterized in that, the described high-temperature heat treatment of step (1) is to be 0.1-0.9g.cm with density
-3Carbon fabric perform place the pyrographite stove in 2000-2300 ℃ the insulation 1-3h.
3. preparation method according to claim 2 is characterized in that, during high-temperature heat treatment, temperature rise rate from the room temperature to 2000-2300 ℃ is 5-10 ℃/min, and soaking time is 1-3h, and rate of temperature fall is 5-8 ℃/min, when temperature is down to 1200 ℃, furnace cooling.
4. preparation method according to claim 1 is characterized in that, adopts the chemical vapor infiltration deposition to obtain low-density carbon/carbon composite in the step (2).
5. preparation method according to claim 4 is characterized in that, step (2) concrete steps are as follows: take hydrogen as carrier gas, propylene or methane are carbon-source gas, with the cvd furnace internal reaction deposition RESEARCH OF PYROCARBON of carbon fabric perform at high temperature.
6. preparation method according to claim 5 is characterized in that, temperature is 1000-1300 ℃ in the cvd furnace, and furnace pressure is 0.3-3.8Kpa, and the reaction times is 60-300h.
7. preparation method according to claim 1, it is characterized in that, step (3) concrete steps are as follows: at first take by weighing the zirtan powder, the 2-4 of consumption take preparing low-density carbon/carbon composite weight as benchmark doubly, alloy powder is placed the compacting of graphite tank, and after placing preparing low-density carbon/carbon composite on the alloy powder, the graphite tank is placed in the High Temperature Furnaces Heating Apparatus heat-treats; Treatment temp is 1900-2300 ℃, and soaking time is 0.5-4h, omnidistance argon shield.
8. preparation method according to claim 7 is characterized in that, temperature rise rate is 5-15 ℃/min during thermal treatment, and rate of temperature fall is 3-8 ℃/min, when being cooled to 600-900 ℃, and furnace cooling.
9. preparation method according to claim 1 is characterized in that, described zirtan powder is prepared from by in the following dual mode any:
(1) zirconium ingot of purity 〉=99.9% and the ratio of titanium ingot take the Zr:Ti molecular ratio as 0.4-9 of purity 〉=99.9% are placed vacuum melting furnace, utilizing the standby alloy powder of aerosolization legal system behind the 1900-2300 ℃ of melting 1-3h under the argon shield condition, alloy powder is crossed 325 orders;
(2) with the zirconium powder of purity 〉=99.9% and the titanium valve of purity 〉=99.9%, the ball milling on high-energy planetary formula ball mill of the ratio take the Zr:Ti molecular ratio as 0.4-9 makes; Zirconium powder and titanium valve and the alloy powder that obtains are all crossed 325 mesh sieves; Rotational speed of ball-mill is 200-500r/min, and Ball-milling Time is 10h-25h, and ratio of grinding media to material is 4-10, and ball-milling medium is the argon shield dry grinding.
10. the anti-ablation carbon/carbon composite of zirconium titanium carbide modification is characterized in that, is the anti-ablation carbon/carbon composite of zirconium titanium carbide modification that is prepared from by the described method of claim 1-9 any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105323908A CN103044054A (en) | 2012-12-11 | 2012-12-11 | Zirconium-titanium carbide-modified anti-ablative carbon/carbon composite material and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105323908A CN103044054A (en) | 2012-12-11 | 2012-12-11 | Zirconium-titanium carbide-modified anti-ablative carbon/carbon composite material and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103044054A true CN103044054A (en) | 2013-04-17 |
Family
ID=48056942
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105323908A Pending CN103044054A (en) | 2012-12-11 | 2012-12-11 | Zirconium-titanium carbide-modified anti-ablative carbon/carbon composite material and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103044054A (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103724039A (en) * | 2013-07-23 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | C/C-ZrC ceramic-based composite material capable of transmitting cooling liquid or gas and preparation method for C/C-ZrC ceramic-based composite material |
| CN104671815A (en) * | 2015-01-19 | 2015-06-03 | 中南大学 | ZrC-TiC modified C/C-SiC composite material and preparation method thereof |
| CN104671814A (en) * | 2015-01-19 | 2015-06-03 | 中南大学 | C/C-SiC-ZrC-TiC composite material and preparation method thereof |
| CN104909793A (en) * | 2015-05-27 | 2015-09-16 | 哈尔滨工业大学 | Ablation resistance composite material and preparation method thereof |
| CN104962796A (en) * | 2015-06-30 | 2015-10-07 | 苏州乔纳森新材料科技有限公司 | Medical titanium alloy and preparing method thereof |
| CN105418126A (en) * | 2016-01-11 | 2016-03-23 | 山东理工大学 | Preparation method for ultrasonically dispersed niobium boride-boron carbide-carbon fiber friction material |
| CN105418113A (en) * | 2016-01-11 | 2016-03-23 | 山东理工大学 | Preparing method for ethanol-dispersed hafnium boride silicon carbide and carbon fiber friction material |
| CN105418120A (en) * | 2016-01-11 | 2016-03-23 | 山东理工大学 | Preparing method of synthetic-fat dispersion zirconium carbide and boron carbide-carbon fiber friction material |
| CN105622152A (en) * | 2016-01-11 | 2016-06-01 | 山东理工大学 | Preparation method of ultrasonically-dispersed titanium carbide and boron carbide-carbon fiber friction material |
| CN107021773A (en) * | 2017-05-22 | 2017-08-08 | 中南大学 | A kind of modified anti-yaw damper carbon/carbon composite of novel super-high temperature ceramics integration and preparation method thereof |
| CN108147842A (en) * | 2018-01-09 | 2018-06-12 | 中南大学 | The preparation method of integrated anti-yaw damper ZrC/SiC-C/C composite materials |
| CN109912313A (en) * | 2019-03-06 | 2019-06-21 | 中南大学 | A kind of single-phase superhigh temperature ceramics modifying carbon/carbon composite material of new multicomponent and preparation method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102203879A (en) * | 2008-09-18 | 2011-09-28 | 原子能与可替代能源委员会 | Nuclear fuel sheath with high heat conductivity and method for making same |
-
2012
- 2012-12-11 CN CN2012105323908A patent/CN103044054A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102203879A (en) * | 2008-09-18 | 2011-09-28 | 原子能与可替代能源委员会 | Nuclear fuel sheath with high heat conductivity and method for making same |
Non-Patent Citations (4)
| Title |
|---|
| 《Carbon》 20121201 Yi Zeng et.al. Microstructure and ablation behavior of carbon/carbon composites infiltrated with Zr-Ti 300-309 1-10 第54卷, * |
| 《Ceramics International》 20120530 Huilong Pi et.al. C/SiC-ZrB2-ZrC composites fabricated by reactive melt infiltration with ZrSi2 alloy 6541-6548 1-10 第38卷, 第8期 * |
| HUILONG PI ET.AL.: "C/SiC–ZrB2–ZrC composites fabricated by reactive melt infiltration with ZrSi2 alloy", 《CERAMICS INTERNATIONAL》 * |
| YI ZENG ET.AL.: "Microstructure and ablation behavior of carbon/carbon composites infiltrated with Zr–Ti", 《CARBON》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103724039A (en) * | 2013-07-23 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | C/C-ZrC ceramic-based composite material capable of transmitting cooling liquid or gas and preparation method for C/C-ZrC ceramic-based composite material |
| CN104671814B (en) * | 2015-01-19 | 2016-10-26 | 中南大学 | A kind of C/C-SiC-ZrC-TiC composite and preparation method thereof |
| CN104671815A (en) * | 2015-01-19 | 2015-06-03 | 中南大学 | ZrC-TiC modified C/C-SiC composite material and preparation method thereof |
| CN104671814A (en) * | 2015-01-19 | 2015-06-03 | 中南大学 | C/C-SiC-ZrC-TiC composite material and preparation method thereof |
| CN104909793A (en) * | 2015-05-27 | 2015-09-16 | 哈尔滨工业大学 | Ablation resistance composite material and preparation method thereof |
| CN104909793B (en) * | 2015-05-27 | 2017-04-26 | 哈尔滨工业大学 | Ablation resistance composite material and preparation method thereof |
| CN104962796A (en) * | 2015-06-30 | 2015-10-07 | 苏州乔纳森新材料科技有限公司 | Medical titanium alloy and preparing method thereof |
| CN105418126A (en) * | 2016-01-11 | 2016-03-23 | 山东理工大学 | Preparation method for ultrasonically dispersed niobium boride-boron carbide-carbon fiber friction material |
| CN105418113A (en) * | 2016-01-11 | 2016-03-23 | 山东理工大学 | Preparing method for ethanol-dispersed hafnium boride silicon carbide and carbon fiber friction material |
| CN105418120A (en) * | 2016-01-11 | 2016-03-23 | 山东理工大学 | Preparing method of synthetic-fat dispersion zirconium carbide and boron carbide-carbon fiber friction material |
| CN105622152A (en) * | 2016-01-11 | 2016-06-01 | 山东理工大学 | Preparation method of ultrasonically-dispersed titanium carbide and boron carbide-carbon fiber friction material |
| CN105622152B (en) * | 2016-01-11 | 2018-02-02 | 山东理工大学 | Ultrasonic wave disperses the preparation method of titanium carbide boron carbide carbon fiber friction material |
| CN107021773A (en) * | 2017-05-22 | 2017-08-08 | 中南大学 | A kind of modified anti-yaw damper carbon/carbon composite of novel super-high temperature ceramics integration and preparation method thereof |
| CN108147842A (en) * | 2018-01-09 | 2018-06-12 | 中南大学 | The preparation method of integrated anti-yaw damper ZrC/SiC-C/C composite materials |
| CN109912313A (en) * | 2019-03-06 | 2019-06-21 | 中南大学 | A kind of single-phase superhigh temperature ceramics modifying carbon/carbon composite material of new multicomponent and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103044054A (en) | Zirconium-titanium carbide-modified anti-ablative carbon/carbon composite material and preparation method thereof | |
| CN107021773B (en) | A kind of modified anti-yaw damper carbon/carbon composite of novel super-high temperature ceramics integration and preparation method thereof | |
| Koyanagi et al. | Additive manufacturing of silicon carbide for nuclear applications | |
| Xie et al. | Ablation behavior and mechanism of C/C–ZrC–SiC composites under an oxyacetylene torch at 3000 C | |
| Avincola et al. | Oxidation at high temperatures in steam atmosphere and quench of silicon carbide composites for nuclear application | |
| Wang et al. | A CrSi2-HfB2-SiC coating providing oxidation and ablation protection over 1973 K for SiC coated C/C composites | |
| CN102503581B (en) | Long-term high-temperature oxidation-resistant multi-element composite ceramic coating for carbon/carbon composite material and preparation and application methods thereof | |
| Wang et al. | Oxidation behavior and microstructural evolution of plasma sprayed La2O3-MoSi2-SiC coating on carbon/carbon composites | |
| Zhang et al. | Microstructure and oxidation behavior of C/C–ZrB2–SiC composites coated with SiC coating at high temperature | |
| CN104671815B (en) | ZrC-TiC modified C/C-SiC composite material and preparation method thereof | |
| CN109912313A (en) | A kind of single-phase superhigh temperature ceramics modifying carbon/carbon composite material of new multicomponent and preparation method thereof | |
| CN102815971B (en) | Hf (Ta) C ultra-high-temperature composite coating and preparation method thereof | |
| CN103193497B (en) | Sticky product with silicon erosion resistance of carbon/carbon composite material and preparation method thereof | |
| Feng et al. | Ablation behavior of single and alternate multilayered ZrC-SiC coatings under oxyacetylene torch | |
| Sun et al. | Ablation mechanism and properties of SiO2 modified ZrB2-SiC coatings fabricated on C/C composites via plasma spraying technology | |
| CN105481477B (en) | A kind of preparation method of graphite/SiC ceramic matrix composite material | |
| Xie et al. | Cyclic ablation behavior of C/C–ZrC–SiC composites under oxyacetylene torch | |
| He et al. | Influence of carbon preform density on the microstructure and ablation resistance of CLVD-C/C-ZrC-SiC composites | |
| Wang et al. | Oxidation and ablation resistant properties of pack-siliconized Si-C protective coating for carbon/carbon composites | |
| Chang et al. | A novel design of Al-Cr alloy surface sealing for ablation resistant C/C-ZrC-SiC composite | |
| Zhong et al. | Local anti-ablation modification of uneven-density C/C composites with the ZrC-SiC composite ceramics | |
| Niu et al. | Microstructure characteristics of silicon carbide coatings fabricated on C/C composites by plasma spraying technology | |
| Wang et al. | Preparation and ablation properties of ZrB2–SiC protective laminae for carbon/carbon composites | |
| CN109485423A (en) | The preparation method of SiC nanowire toughening chemical gaseous phase co-deposition HfC-SiC duplex heat treatment | |
| Tong et al. | Effect of PyC-SiC double-layer interface on ablation behaviour of impacted CVD-SiCnws/HfC coating |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130417 |