CN108409359B - Ablation-resistant ternary consumption powder and application - Google Patents
Ablation-resistant ternary consumption powder and application Download PDFInfo
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- 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
- C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
- C04B41/51—Metallising, e.g. infiltration of sintered ceramic preforms with molten metal
- C04B41/515—Other specific metals
- C04B41/5155—Aluminium
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- C—CHEMISTRY; METALLURGY
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- 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
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- 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
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Abstract
The invention discloses ablation-resistant ternary powder and application, belongs to the field of light ablation-resistant dissipation heat-proof composite materials, and particularly relates to ablation-resistant powder and application. Aims to solve the problems of low content of a dissipative agent in a matrix of the dissipative heat-proof composite material and high line ablation rate. The powder consumption alloy system comprises aluminum, silicon and boron, the ternary powder consumption is applied to the dissipation heat-proof composite material, and the application method comprises the following steps: firstly, preparing powder consumption agent; secondly, processing the base material; thirdly, processing the graphite crucible; and fourthly, vacuum pressure infiltration. The invention provides a novel ternary dissipation powder based on a dissipation heat protection mechanism, which can form a heat dissipation and oxygen dissipation liquid ceramic protective layer under the conditions of high temperature, high pressure and high-speed particle flow scouring, and the prepared light ablation-resistant dissipation heat protection composite material is used for manufacturing a throat liner of a solid rocket engine spray pipe, a gas vane, an end cap of a hypersonic aircraft, a wing leading edge, a tail vane and a steering orifice plate component of a missile.
Description
Technical Field
The invention belongs to the field of light ablation-resistant dissipation heat-proof composite materials, and particularly relates to ablation-resistant dissipation powder and application thereof.
Background
The ablation-resistant material is an important engineering material in the fields of national defense and aerospace, and has the function that the pneumatic appearance of a heated component can be maintained in the working time under the conditions of high temperature and high-speed airflow scouring so that an aircraft can normally work. With the continuous development of aerospace technology, increasingly strict requirements are put on ablation-resistant materials. The traditional ablation-resistant material mainly comprises refractory metal and composite materials thereof, ceramic matrix composite materials, resin matrix composite materials, tungsten infiltrated copper, carbon/carbon composite materials and the like. The ablation resistance mechanism of the material is characterized by each material. Refractory metals such as tungsten, molybdenum, niobium and composite materials thereof mainly absorb heat by a heat sink, but have high density and do not meet the light weight requirement of aircraft parts; the ceramic matrix composite is mainly based on a radiation heat-proof mechanism, but the ceramic has poor heat shock resistance and is difficult to machine; the resin-based composite material generally absorbs external heat through thermal desorption, so that the ablation rate is high; the heat-proof mechanism of the tungsten copper infiltration material is sweating heat-proof and heat sink heat-proof; the carbon/carbon and modified composite material thereof are mainly radiation and ablation type heat-proof mechanisms, but the preparation process is complex and the cost is high.
The dissipative heat-proof composite material is a novel ablation-resistant material, and can meet the use requirements of components such as the wing leading edge of a hypersonic aircraft, a rocket engine combustion chamber, a missile steering orifice plate, a gas vane and the like. The heat protection mechanism of the dissipation heat protection composite material is that a substance with Gibbs oxidation free energy lower than that of a matrix is permeated into the matrix of porous graphite or low-density carbon to serve as a dissipation agent, and in the high-temperature ablation process, the dissipation agent is liquefied and gasified to absorb certain aerodynamic heat to form heat dissipation; the dispersing agent is preferentially reacted with the oxygen of the boundary layer to consume the oxygen of the boundary layer to form oxygen dissipation; meanwhile, the liquid ceramic generated by the oxidation of the dissipative agent can form a protective layer on the surface of the substrate, so that the ablation resistance of the substrate is further improved. Under the conditions of high pressure and high-speed particle flow scouring, the liquid ceramic layer can be continuously scoured, meanwhile, the dissipater in the base body continuously overflows to consume heat and oxygen and form a new ceramic layer, and a nonequilibrium thermodynamic dissipater structure is formed within a certain time. However, the existing dissipation agent has poor wettability with the matrix, and interface reaction is easy to occur in the process of infiltration of the dissipation agent into the matrix, so that the dissipation agent infiltrated into the matrix undergoes volume expansion to block an infiltration channel, and thus the content of the dissipation agent in the matrix of the existing dissipation heat-proof composite material is low; meanwhile, in the preparation process of the existing dissipation heat-proof composite material, external pressure is not applied in the infiltration process of the dissipation agent, so that the problem of low content of the dissipation agent in the matrix can be caused, and the low content of the dissipation agent in the matrix causes high ablation rate of the dissipation heat-proof composite material.
Disclosure of Invention
The invention provides an ablation-resistant ternary powder consumption agent and application thereof, aiming at solving the problems that the content of a dissipation agent in a matrix of the existing dissipation heat-proof composite material is low, and the line ablation rate is high due to the low content of the powder consumption agent.
The ablation-resistant ternary dissipative agent comprises, by mass, 4-8 parts of aluminum powder, 11-14 parts of silicon powder and 1-3 parts of boron powder; the particle size of the aluminum powder is less than 3 mm; the grain size of the silicon powder is less than 3 mm; the particle size of the boron powder is less than 3 mm.
The application of the ternary dissipation agent in preparing a dissipation heat-proof composite material;
the method for preparing the dissipation heat-proof composite material by using the ternary dissipation agent specifically comprises the following steps:
weighing 4-8 parts of aluminum, 11-14 parts of silicon and 1-3 parts of boron in parts by weight, and uniformly mixing to obtain a ternary consumption powder;
secondly, processing the porous matrix into a component, ultrasonically cleaning the component, drying the component, and mounting the component on a hanger rod in an air pressure infiltration furnace after drying;
the porous matrix is graphite or a low-density C/C composite material; the density of the low-density C/C composite material is 1.5-1.8 g/cm3；
The density of the graphite is 1.65-1.92 g/cm3；
The porosity of the porous matrix is 15-40%;
the drying temperature is 80-100 ℃, and the drying time is 2-4 h;
thirdly, placing the graphite crucible into an air pressure infiltration furnace, and coating a boron nitride release agent on the inner wall of the graphite crucible;
fourthly, placing the dissipative agent obtained in the first step into the graphite crucible treated in the third step, heating to 1400-1800 ℃ at a heating rate of 10-30 ℃/min under a vacuum condition, after the dissipative agent is melted, immersing the member obtained in the second step into the melted dissipative agent for air pressure infiltration, finally extracting the member from the melted dissipative agent, and cooling to obtain the dissipative heat-proof composite material;
the atmosphere of the air pressure infiltration furnace during air pressure infiltration is argon atmosphere, the infiltration pressure is 20-100 atmospheric pressure, the infiltration time is 5-20 min, and the infiltration temperature is 1400-1800 ℃.
The principle and the beneficial effects of the invention are as follows:
1. compared with the aluminum-silicon binary powder, the aluminum-silicon-boron ternary powder has higher melting point and can adapt to the ablation environment at higher temperature; the addition of boron can improve the wettability of the powder consumption agent and the matrix, improve the infiltration rate, form a liquid ceramic protective layer with larger adhesive force on the surface of the matrix in an ablation environment, resist airflow scouring and better protect the matrix; boron has high melting latent heat and vaporization latent heat, and can well play a role in heat dissipation; the physical properties of the components of the ablation-resistant ternary dissipative agent alloy are shown in table 1, in the ablation-resistant ternary dissipative agent, the melting latent heat and the vaporization latent heat of Si and B are high, the heat dissipation effect is large, and Al, Si and B react with oxygen before C in an ablation environment, so that the purpose of oxygen dissipation can be achieved.
2. According to the invention, a dissipation agent is immersed into a carbon material matrix by using a vacuum air pressure infiltration method to form a dissipation heat-proof composite material, the ablation-resistant ternary dissipation agent in the dissipation heat-proof composite material can form a heat-dissipation and oxygen-dissipation liquid ceramic protective layer under the conditions of high temperature, high pressure and high-speed particle flow scouring, and the formed liquid ceramic protective layer has larger adhesive force, can resist airflow scouring and better protects the matrix;
3. the ablation-resistant ternary consumption powder is applied to preparation of a dissipation heat-proof composite material, the infiltration effect is good, and the highest mass infiltration rate can reach 33.39%; under the condition of oxyacetylene ablation, after the dissipative heat-proof composite material prepared by the invention is ablated for 100s, the linear ablation rate is reduced to 1.0 μm/s from 78.4 μm/s of the original matrix, so that the linear ablation rate is improved by one order of magnitude, and the dissipative heat-proof composite material has excellent ablation resistance;
4. the composite material prepared from the ternary powder can be used for manufacturing a throat liner and a gas rudder of a solid rocket engine spray pipe, and can also be used for manufacturing components such as an end cap, a wing front edge, a tail rudder of a hypersonic aircraft, a steering orifice plate for manufacturing a missile and the like.
Description of the drawings:
FIG. 1 graph of oxidation free energy versus temperature for the dispersant and matrix in example 1; curve 1 in the figure is C + O2＝CO2Free energy of reaction of (a); 2 is 4/3B + O2＝2/3B2O3Free energy of reaction of (a); 3 is Si + O2＝SiO2Free energy of reaction of (a); 4 is 4/3Al + O2＝2/3Al2O2Free energy of reaction of (a);
FIG. 2 is a macro topography after ablation of the C/C substrate in example 1;
FIG. 3 shows C/C-Al in example 17Si11B2Macro morphology of the composite material after ablation.
The specific implementation mode is as follows:
the technical scheme of the invention is not limited to the specific embodiments listed below, and any reasonable combination of the specific embodiments is included.
The first embodiment is as follows: the ablation-resistant ternary dissipative agent comprises, by mass, 4-8 parts of aluminum powder, 11-14 parts of silicon powder and 1-3 parts of boron powder.
The principle and the beneficial effects of the implementation mode are as follows:
1. compared with the aluminum-silicon binary powder, the aluminum-silicon-boron ternary powder has higher melting point and can adapt to the ablation environment at higher temperature; the addition of boron can improve the wettability of the powder consumption agent and the matrix, improve the infiltration rate, form a liquid ceramic protective layer with larger adhesive force on the surface of the matrix in an ablation environment, resist airflow scouring and better protect the matrix; boron has high melting latent heat and vaporization latent heat, and can well play a role in heat dissipation; the physical properties of the ablation-resistant ternary dissipative agent alloy components are shown in Table 1, in the ablation-resistant ternary dissipative agent, the melting latent heat and the vaporization latent heat of Si and B are high, the heat dissipation effect is large, and Al, Si and B react with oxygen before C in an ablation environment, so that the purpose of oxygen dissipation can be achieved;
2. the dissipation heat-proof composite material prepared by the ablation-resistant ternary powder has good infiltration effect, the mass infiltration rate can reach as high as 33.39%, the linear ablation rate of the dissipation heat-proof composite material is reduced to 1.0 μm/s from 78.4 μm/s of the original matrix after the dissipation heat-proof composite material is ablated for 100s under the oxyacetylene ablation condition, the order of magnitude is improved, and the dissipation heat-proof composite material has excellent ablation resistance;
3. the composite material prepared from the ternary powder can be used for manufacturing a throat liner and a gas rudder of a solid rocket engine spray pipe, and can also be used for manufacturing components such as an end cap, a wing front edge and a tail rudder of a hypersonic aircraft, a steering orifice plate for manufacturing a missile and the like.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: the particle size of the aluminum powder is less than 3 mm; the grain size of the silicon powder is less than 3 mm; the particle size of the boron powder is less than 3 mm. Other steps and parameters are the same as in the first embodiment.
The third concrete implementation mode: the ablation-resistant ternary dissipation agent is applied to preparation of a dissipation heat-proof composite material.
The fourth concrete implementation mode: the third difference between the present embodiment and the specific embodiment is that: the method for preparing the dissipative heat-proof composite material by using the ternary dissipative agent comprises the following steps:
weighing 4-8 parts of aluminum, 11-14 parts of silicon and 1-3 parts of boron in parts by weight, and uniformly mixing to obtain a ternary consumption powder;
secondly, processing the porous matrix into a component, ultrasonically cleaning the component, drying the component, and mounting the component on a hanger rod in an air pressure infiltration furnace after drying;
thirdly, placing the graphite crucible into an air pressure infiltration furnace, and coating a boron nitride release agent on the inner wall of the graphite crucible;
and fourthly, placing the dissipative agent obtained in the first step into the graphite crucible treated in the third step, heating to 1400-1800 ℃ at a heating rate of 10-30 ℃/min under a vacuum condition, after the dissipative agent is melted, immersing the member obtained in the second step into the melted dissipative agent for air pressure infiltration, finally, taking out the member from the melted dissipative agent, and cooling to obtain the dissipative heat-proof composite material. Other steps and parameters are the same as those in the third embodiment.
The principle and the beneficial effects of the implementation mode are as follows:
1. according to the embodiment, a dissipation agent is immersed into a carbon material matrix by using a vacuum air pressure infiltration method to form a dissipation heat-proof composite material, the dissipation agent is immersed into the matrix by using the vacuum air pressure infiltration method to form the dissipation heat-proof composite material, the ablation-resistant ternary dissipation agent in the dissipation heat-proof composite material can form a heat-dissipation and oxygen-dissipation liquid ceramic protective layer under the conditions of high-temperature, high-pressure and high-speed particle flow scouring, the formed liquid ceramic protective layer has larger adhesive force, can resist air flow scouring and better protects the matrix;
2. the ablation-resistant ternary powder is applied to preparation of the dissipation heat-proof composite material, the infiltration effect is good, and the highest mass infiltration rate can reach 33.39%; under the condition of oxyacetylene ablation, after the dissipative heat-proof composite material prepared by the invention is ablated for 100s, the linear ablation rate is reduced to 1.0 μm/s from 78.4 μm/s of the original matrix, so that the linear ablation rate is improved by one order of magnitude, and the dissipative heat-proof composite material has excellent ablation resistance;
3. the ablation-resistant heat dissipation-resistant composite material prepared by the embodiment can be used for manufacturing a throat liner and a gas vane of a solid rocket engine spray pipe, and can also be used for manufacturing components such as an end cap, a wing front edge, a tail vane of a hypersonic aircraft, a steering orifice plate for manufacturing a missile and the like.
The fifth concrete implementation mode: the fourth difference between this embodiment and the specific embodiment is that: and step two, the porous matrix is graphite or a low-density C/C composite material. Other steps and parameters are the same as in embodiment four.
The sixth specific implementation mode: the fifth embodiment is different from the fifth embodiment in that: the density of the low-density C/C composite material is 1.5-1.8 g/cm3. Other steps and parameters are the same as those in the fifth embodiment.
The seventh embodiment: the fifth embodiment is different from the fifth embodiment in that: the density of the graphite is 1.65-1.92 g/cm3. Other steps and parameters are the same as those in the fifth embodiment.
The specific implementation mode is eight: the fourth difference between this embodiment and the specific embodiment is that: and step two, the porosity of the porous matrix is 15-40%. Other steps and parameters are the same as in embodiment four.
The specific implementation method nine: the fourth difference between this embodiment and the specific embodiment is that: and step two, the drying temperature is 80-100 ℃, and the drying time is 2-4 h. Other steps and parameters are the same as in embodiment four.
The detailed implementation mode is ten: the fourth difference between this embodiment and the specific embodiment is that: and fourthly, during the air pressure infiltration, the atmosphere of the air pressure infiltration furnace is argon atmosphere, the infiltration pressure is 20-100 atm, the infiltration time is 5-20 min, and the infiltration temperature is 1400-1800 ℃. Other steps and parameters are the same as in embodiment four.
The following examples were used to demonstrate the beneficial effects of the present invention:
the first embodiment is as follows:
the method for preparing the dissipative heat-proof composite material by using the ternary dissipative agent in the embodiment specifically comprises the following steps:
weighing 7 parts of aluminum, 11 parts of silicon and 2 parts of boron according to the parts by weight, and uniformly mixing to obtain a ternary powder;
the particle size of the aluminum powder is less than 3 mm; the grain size of the silicon powder is less than 3 mm; the particle size of the boron powder is less than 3 mm;
secondly, processing the porous matrix into a component, ultrasonically cleaning the component, drying the component, and mounting the component on a hanger rod in an air pressure infiltration furnace after drying;
the porous matrix is a low-density C/C composite material; the density of the low-density C/C composite material is 1.63g/cm3；
The porosity of the porous matrix is 26%;
the drying temperature is 80 ℃, and the drying time is 4 hours;
thirdly, placing the graphite crucible into an air pressure infiltration furnace, and coating a boron nitride release agent on the inner wall of the graphite crucible;
fourthly, placing the dissipative agent obtained in the first step into the graphite crucible processed in the third step, heating the dissipative agent to 1700 ℃ at a heating rate of 20 ℃/min under a vacuum condition, after the dissipative agent is melted, immersing the member obtained in the second step into the melted dissipative agent for air pressure infiltration, finally taking out the member from the melted dissipative agent, and cooling to obtain the dissipative heat-proof composite material;
the atmosphere of the air pressure infiltration furnace during the air pressure infiltration is argon atmosphere, the infiltration pressure is 100 atmospheric pressure, the infiltration time is 15min, and the infiltration temperature is 1700 ℃.
In the embodiment, the mass of the impregnated dissipation heat-proof composite material is increased from 12.01g of the original matrix to 16.02g, and the mass of the impregnated dissipation agent reaches 33.39% of the mass of the matrix; according to the GJB 323A-96 standard of the state military, the dissipative heat-proof composite material oxyacetylene ablation test is carried out, under the oxyacetylene ablation condition, the ablation is carried out for 100s, the line ablation rate is reduced to 1.0 μm/s from 78.4 μm/s of the original matrix, and the line ablation rate is improved by more than one order of magnitude;
FIG. 1 is the free energy of oxidation versus temperature curve for the dispersant and the matrix in example 1. it can be seen from FIG. 1 that in the ablative environment, Al, Si and B react with oxygen before C, especially Al, to achieve the purpose of oxygen dissipation;
FIGS. 2 and 3 are respectively a C/C substrate and C/C-Al7Si11B2The macroscopic appearance graph of the ablated composite material shows that the C/C matrix is burnt to form obvious ablation pits after being ablated by times, and is impregnated with Al7Si11B2The surface of the composite material of the ternary powder consumption agent has no ablation pits, and only a few of powder consumption agents which are condensed after being melted are used, so that the dissipation agent protects the matrix in the ablation process and plays a role in dissipation and heat prevention.
Example two:
the method for preparing the dissipative heat-proof composite material by using the ternary dissipative agent in the embodiment specifically comprises the following steps:
weighing 5 parts of aluminum, 12 parts of silicon and 3 parts of boron according to the parts by weight, and uniformly mixing to obtain a ternary powder;
the particle size of the aluminum powder is less than 3 mm; the grain size of the silicon powder is less than 3 mm; the particle size of the boron powder is less than 3 mm;
secondly, processing the porous matrix into a component, ultrasonically cleaning the component, drying the component, and mounting the component on a hanger rod in an air pressure infiltration furnace after drying;
the porous matrix is graphite; the density of the graphite was 1.75g/cm3；
The porosity of the porous matrix is 20.5%;
the drying temperature is 80 ℃, and the drying time is 4 hours;
thirdly, placing the graphite crucible into an air pressure infiltration furnace, and coating a boron nitride release agent on the inner wall of the graphite crucible;
fourthly, placing the dissipative agent obtained in the first step into the graphite crucible processed in the third step, heating to 1800 ℃ at a heating rate of 20 ℃/min under a vacuum condition, after the dissipative agent is melted, immersing the member obtained in the second step into the melted dissipative agent for air pressure infiltration, finally taking out the member from the melted dissipative agent, and cooling to obtain the dissipative heat-proof composite material;
the atmosphere of the air pressure infiltration furnace during the air pressure infiltration is argon atmosphere, the infiltration pressure is 20 atm, the infiltration time is 5min, and the infiltration temperature is 1800 ℃.
In the embodiment, the mass of the impregnated dissipation heat-proof composite material is increased from 12.53g of the original matrix to 16.37g, and the mass of the impregnated dissipation agent reaches 30.65% of the mass of the matrix; according to the GJB 323A-96 standard of the state military, the dissipative heat-proof composite material oxyacetylene ablation test is carried out, under the oxyacetylene ablation condition, the ablation time is 100s, the line ablation rate is reduced to 0.3 μm/s from 19.9 μm/s of the original matrix, and the line ablation rate is improved by more than one order of magnitude.
TABLE 1
Claims (4)
1. The ablation-resistant ternary consumption powder is characterized in that: the ablation-resistant ternary dissipative agent comprises 4-8 parts of aluminum powder, 11-14 parts of silicon powder and 1-3 parts of boron powder in parts by mass;
the method for preparing the dissipative heat-proof composite material by using the ablation-resistant ternary dissipative agent comprises the following steps:
weighing 4-8 parts of aluminum, 11-14 parts of silicon and 1-3 parts of boron in parts by weight, and uniformly mixing to obtain a ternary consumption powder;
secondly, processing the porous matrix into a component, ultrasonically cleaning the component, drying the component, and mounting the component on a hanger rod in an air pressure infiltration furnace after drying;
thirdly, placing the graphite crucible into an air pressure infiltration furnace, and coating a boron nitride release agent on the inner wall of the graphite crucible;
fourthly, placing the dissipative agent obtained in the first step into the graphite crucible treated in the third step, heating to 1400-1800 ℃ at a heating rate of 10-30 ℃/min under a vacuum condition, after the dissipative agent is melted, immersing the member obtained in the second step into the melted dissipative agent for air pressure infiltration, finally extracting the member from the melted dissipative agent, and cooling to obtain the dissipative heat-proof composite material;
step two, the porous matrix is graphite or a low-density C/C composite material; the density of the low-density C/C composite material is 1.5-1.8 g/cm3(ii) a The density of the graphite is 1.65-1.75 g/cm3；
In the second step, the porosity of the porous matrix is 15-40%;
and fourthly, during the air pressure infiltration, the atmosphere of the air pressure infiltration furnace is argon atmosphere, the infiltration pressure is 20-100 atm, the infiltration time is 5-20 min, and the infiltration temperature is 1400-1800 ℃.
2. The ablation-resistant ternary dissipation agent of claim 1, wherein: the particle size of the aluminum powder is less than 3 mm; the grain size of the silicon powder is less than 3 mm; the particle size of the boron powder is less than 3 mm.
3. Use of the ablation-resistant ternary dissipation agent of claim 1 in the preparation of a dissipative heat protective composite, wherein: the method for preparing the dissipative heat-proof composite material by using the ternary dissipative agent comprises the following steps:
weighing 4-8 parts of aluminum, 11-14 parts of silicon and 1-3 parts of boron in parts by weight, and uniformly mixing to obtain a ternary consumption powder;
secondly, processing the porous matrix into a component, ultrasonically cleaning the component, drying the component, and mounting the component on a hanger rod in an air pressure infiltration furnace after drying;
thirdly, placing the graphite crucible into an air pressure infiltration furnace, and coating a boron nitride release agent on the inner wall of the graphite crucible;
and fourthly, placing the dissipative agent obtained in the first step into the graphite crucible treated in the third step, heating to 1400-1800 ℃ at a heating rate of 10-30 ℃/min under a vacuum condition, after the dissipative agent is melted, immersing the member obtained in the second step into the melted dissipative agent for air pressure infiltration, finally, taking out the member from the melted dissipative agent, and cooling to obtain the dissipative heat-proof composite material.
4. Use of the ablation-resistant ternary dissipation agent according to claim 3 in the preparation of a dissipative heat protection composite, characterized in that: and step two, the drying temperature is 80-100 ℃, and the drying time is 2-4 h.
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| RU2178394C2 (en) * | 1996-10-22 | 2002-01-20 | Сосьете Насьональ Д`Этюд Э Де Констрюксьон Де Мотер Д`Авиасьон - С.Н.Е.К.М.А. | Thermochemical treatment of nonporous, slightly porous or highly porous carbon material |
| CN101306959A (en) * | 2008-07-07 | 2008-11-19 | 中国人民解放军国防科学技术大学 | Method for preparing superhigh temperature resistant ceramic coat |
| CN104402525A (en) * | 2014-10-30 | 2015-03-11 | 中国人民解放军国防科学技术大学 | Graphite surface ablation-resistant layer and preparation method thereof |
| CN107311684A (en) * | 2017-07-24 | 2017-11-03 | 哈尔滨工业大学 | A kind of dissipation heat-resistant composite material and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2178394C2 (en) * | 1996-10-22 | 2002-01-20 | Сосьете Насьональ Д`Этюд Э Де Констрюксьон Де Мотер Д`Авиасьон - С.Н.Е.К.М.А. | Thermochemical treatment of nonporous, slightly porous or highly porous carbon material |
| CN101306959A (en) * | 2008-07-07 | 2008-11-19 | 中国人民解放军国防科学技术大学 | Method for preparing superhigh temperature resistant ceramic coat |
| CN104402525A (en) * | 2014-10-30 | 2015-03-11 | 中国人民解放军国防科学技术大学 | Graphite surface ablation-resistant layer and preparation method thereof |
| CN107311684A (en) * | 2017-07-24 | 2017-11-03 | 哈尔滨工业大学 | A kind of dissipation heat-resistant composite material and preparation method thereof |
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