CN115557800B - Method for preparing silicon carbide-based composite material by uniformly ceramifying porous carbon - Google Patents
Method for preparing silicon carbide-based composite material by uniformly ceramifying porous carbon Download PDFInfo
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Abstract
The invention relates to a method for preparing a silicon carbide-based composite material by uniformly ceramifying porous carbon, belonging to the technical field of thermal protection materials for aircrafts. According to the method, phenolic resin, ethylene glycol and a curing agent are uniformly mixed to prepare a precursor solution, the precursor solution is immersed into a carbon or ceramic fiber preform, and a high-pressure auxiliary phase separation and high-temperature curing method is adopted, so that the phenolic resin is promoted to participate in polymerization reaction by inhibiting the boiling of the ethylene glycol, the volatilization of free phenol and other substances, and further, after curing-carbonization, the porous carbon-based infiltration preform with a uniform nano-pore structure and proper porosity is obtained. The porous carbon is completely converted into a silicon carbide matrix through low-temperature siliconizing at 1450-1550 ℃, and the original pore canal can be completely filled through volume expansion generated in the process. The obtained silicon carbide substrate has compact structure, no carbon residue and silicon residue, and fine grains; meanwhile, the introduced liquid silicon is completely consumed in the reaction process, and the fiber is not etched.
Description
Technical Field
The invention relates to the technical field of thermal protection materials for aircrafts, in particular to a method for preparing a silicon carbide-based composite material by uniformly ceramifying porous carbon.
Background
In the process of flying near space at high speed or reentering an atmospheric layer, the aircraft faces a severe thermal oxygen environment examination, and the thermal protection system material of the aircraft has the excellent characteristics of high strength and toughness, thermal shock resistance, ultra-high temperature oxidation resistance, ablation resistance and the like. Carbon or silicon carbide fiber reinforced silicon carbide composite materials (C/SiC, siC/SiC) have a series of advantages of low density, high temperature resistance, high strength, oxidation ablation resistance and the like, and therefore, have become important candidate materials in aircraft thermal protection systems. However, the high manufacturing costs and long manufacturing cycles limit the use of silicon carbide based composites on board aircraft. The main preparation technology of the fiber reinforced SiC ceramic matrix composite material comprises the following steps: chemical Vapor Infiltration (CVI), precursor dip cracking (PIP), reactive Melt Infiltration (RMI), slurry Infiltration (SI), and the like. The RMI has the advantages of low preparation cost, short period, capability of realizing near net forming and the like, and is considered as a preparation technology of the SiC ceramic matrix composite material with industrial prospect. However, in the traditional RMI process, the carbon matrix generally adopts resin carbon, pyrolytic carbon and a hybrid matrix thereof, the carbon wall of the matrix framework has thick wall, and a large number of hundred-micron-sized macropores exist, so that the carbon matrix is incomplete in reaction, excessive silicon remains and fiber is etched, and the prepared C/SiC composite material has poor high-temperature mechanical, oxidation and ablation resistance. Articles "Journal of the European Ceramic Society, 2012, 32 (16): 4497-4505" and "Ceramics International, 2017, 43 (7): 5832-5836" indicate that the amount of carbon residue in the produced composite material can be effectively reduced by employing a porous carbon matrix instead of the dense carbon matrix in a conventional preform. However, since many macropores of several micrometers to tens of micrometers remain in the preform, many silicon-rich regions are still commonly present in the prepared composite material, and significant fiber and interface etching occurs. The article "Materials Science and Engineering, 1991, 144:63-74" proposes that the reaction process of carbon and silicon proceeds earlier in the dissolution-precipitation mechanism, and that after a micron-sized dense SiC layer is formed on the surface of carbon particles, the reaction can proceed only by means of diffusion of carbon in the SiC layer, the reaction mechanism is converted to a diffusion mechanism, and the reaction speed in the process is very slow, so that the carbon matrix cannot be completely ceramized. Thus, carbon matrices with nanosized backbones are expected to achieve rapid complete ceramic transformation. Aiming at the problems that the porous carbon is large in pore diameter and skeleton size (micron or near micron) and uneven in distribution and the like in the traditional resin, pore-forming agent and curing agent mixed solution, the invention prepares the porous carbon matrix with nanoscale uniform pores (40-nm) through a pressure-assisted phase separation-high-temperature curing combined technology, and the ideal uniform ceramization of the carbon matrix is realized through the adjustment of the porosity of the matrix and the optimization of a reaction process, so that the fiber-reinforced silicon carbide composite material which is free of fiber etching, compact in matrix, free of carbon residue and silicon residue and fine in grain size (50-100 nm) is finally obtained.
Disclosure of Invention
Aiming at the problems that a carbon matrix cannot be completely ceramic, a large amount of silicon remains in the obtained SiC matrix, fiber etching and the like when the prior RMI process is used for preparing the carbon or ceramic fiber reinforced SiC ceramic matrix composite material, the invention provides a method for preparing the silicon carbide based composite material by uniformly ceramic porous carbon, which has the advantages of low production cost, short preparation period and excellent mechanical property and ablative property.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
the method for preparing the silicon carbide-based composite material by uniformly ceramifying porous carbon comprises the steps of firstly preparing a porous carbon matrix with a porosity of 45-58%, and then performing siliconizing treatment to obtain the silicon carbide-based composite material; the method specifically comprises the following steps:
(1) Dipping treatment: immersing carbon fiber or ceramic fiber preform in precursor solution for a period of time, and taking out;
(2) High-pressure auxiliary phase separation and curing treatment: pressurizing the carbon or ceramic fiber preform soaked with the precursor solution to 1-10 MPa, quickly heating to a curing temperature, and forming a nano-porous organic matrix with uniform pore structure in the fiber preform under the conditions of external pressure and high curing temperature, namely the fiber reinforced nano-porous resin matrix composite material; in the process, the external pressure can inhibit the boiling of glycol and the volatilization of free phenol and other substances in the precursor solution, so that the uniform gel forms a porous organic matrix with uniform pore structure. Meanwhile, the high curing temperature can obviously improve the reactivity of hydroxyl at the chain end of the phenolic resin molecule, so that more active sites participate in polymerization reaction in the phase separation process, the number of nucleation sites in the reaction precursor solution is greatly increased, and a three-dimensional network skeleton with the structural characteristics of small aperture (less than 100 nm) is formed.
(3) Carbonizing: performing high-temperature carbonization treatment on the fiber reinforced nano porous resin matrix composite material obtained in the step (2) to obtain a low-density porous carbon matrix infiltration preform;
(4) Repeating the processes of soaking, curing and carbonizing in the steps (1) - (3) for a plurality of times until a porous carbon-based infiltration preform with a required density is obtained;
(5) Siliconizing treatment: and (3) performing low-temperature fusion siliconizing treatment on the porous carbon-based infiltration preform obtained in the step (4) to obtain the fiber reinforced silicon carbide composite material.
In the step (1), the precursor solution is prepared by uniformly mixing and stirring phenolic resin, glycol and curing agent according to the weight ratio of (10-15): (11-16): (1-2); in the precursor solution, the phenolic resin can be common commercial grade resin or modified boron phenolic aldehyde, barium phenolic aldehyde and the like, and the curing agent is at least one of sodium carbonate, propylene carbonate, p-toluenesulfonic acid, phosphoric acid, benzenesulfonic acid, benzenesulfonyl chloride, hexamethylenetetramine and methylol urea.
In the step (1), the carbon fiber and ceramic fiber preform may have an interface layer, wherein the interface layer is one or more of a pyrolytic carbon interface, a silicon carbide interface, or a boron nitride interface.
In the impregnation treatment in the step (1): the pressure range is 0.1-9 MPa, the soaking time is 1-4 h, and the soaking treatment is finished when no obvious bubbles exist.
In the step (2), the curing temperature is 120-250 ℃, and the heating rate is more than 10 ℃/min; the porous organic matrix on the surface of the fiber has a three-dimensional network skeleton structure with small pore size (< 100 nm) characteristic.
In the step (3), the carbonization treatment process is as follows: and (3) placing the fiber reinforced nano porous resin matrix composite material obtained after the curing treatment in a vacuum carbonization furnace, heating the vacuum carbonization furnace to 1200-1800 ℃ at a heating rate of 5-10 ℃/min, and obtaining a carbon matrix with uniformly distributed nano pores on the surface of the fiber through the pyrolysis of an organic matrix and the combination of micropores at a high temperature, thereby obtaining the porous carbon/carbon composite material (porous carbon matrix infiltration preform).
In the step (4), the pore size distribution range of the carbon matrix in the porous carbon-based infiltration preform is 10-80 nm, and the pore size of the median pore is 40-45 nm.
In the step (5), in the siliconizing treatment process, the siliconizing temperature is 1450-1550 ℃, the heat preservation time is 1-2 h, the grain size of the used silicon powder is 10 mu m-2 mm, and the pressure in the infiltration process is less than 20 Pa. The siliconizing treatment adopts lower reaction temperature, so that silicon carbide can be prevented from being rapidly generated and blocking pore channels in the infiltration process, and further the subsequent liquid silicon infiltration is influenced. And, the lower reaction temperature can inhibit further growth of the produced silicon carbide grains.
In the step (4), the porosity of the porous carbon matrix obtained after carbonization treatment is calculated from the matching relationship between the porosity P and the volume expansion rate of the porous carbon matrix under the ideal condition that the porous carbon generates compact silicon carbide after reaction: p=1-V m C/V m SiC, where V m C is the molar volume of the porous carbon matrix, V m SiC is the dense silicon carbide matrix molar volume.
The silicon carbide substrate obtained in the step (5) is compact, no carbon residue and no silicon residue exist in the silicon carbide substrate, and the grain size of the silicon carbide is 50-100 nm; and after the reaction, the fibers in the composite material are not etched.
The invention has the following beneficial effects:
1. according to the invention, the porous carbon matrix with a uniform nano-pore structure (median pore 40-45 nm) is obtained after high-pressure assisted phase separation, high-temperature solidification and carbonization. Compared with other reaction infiltration methods for preparing C/SiC and SiC/SiC, the porous carbon matrix has the smallest framework size and pore diameter. The small-sized carbon skeleton and pore size are beneficial to complete ceramization of the carbon matrix and complete consumption of liquid silicon.
2. The invention provides and verifies the design criteria of the carbon matrix structure and the reaction infiltration process, and obtains a new preparation method of the high-performance fiber reinforced silicon carbide-based composite material. The invention determines the proper porosity range of an ideal porous carbon matrix through theoretical calculation of silicon-carbon reaction, and obtains the corresponding porous carbon matrix through the combined regulation and control of precursor raw materials and a solidification and carbonization process. The silicon-carbon reaction under nearly ideal state is realized by low-temperature siliconizing: when the reaction is completed, the porous carbon matrix is completely converted into a silicon carbide matrix, and the original pore channels are completely filled by volume expansion caused in the process; meanwhile, the introduced liquid silicon is completely consumed in the reaction process, and the fiber is not etched.
3. The invention prepares a series of high-performance silicon carbide-based composite materials, and the materials are expected to be used as novel high-temperature oxidation-ablation-resistant materials to be applied to the fields of aerospace thermal protection and the like. The C/SiC material prepared by the invention has excellent mechanical properties because the matrix strength is high and the carbon fiber is not damaged. The strength of the C/SiC composite material prepared by taking the T700 12K needled carbon fiber preform as a reinforcement can reach 270 MPa, which is far higher than that of the composite material with the same preform structure prepared by the traditional reaction infiltration method. Meanwhile, the generated silicon carbide substrate is compact, no residual silicon and carbon phase exists in the silicon carbide substrate, the prepared C/SiC has excellent high-temperature ablation resistance, and the linear ablation rate is smaller than 0.02 mu m/s after the silicon carbide substrate is ablated for 500 and s in an oxyacetylene environment with the surface temperature of 2200 ℃ for a long time.
Drawings
FIG. 1 is a graph showing the morphology of the carbon matrix of the carbon/carbon composite material produced in example 1.
FIG. 2 is a pore size distribution of the carbon/carbon composite material produced in example 1.
FIG. 3 is a morphology of the silicon carbide substrate of example 1.
Fig. 4 is a morphology of the carbon fiber reinforced silicon carbide composite of example 1.
FIG. 5 is a pore size distribution of the carbon/carbon composite material produced in example 2.
FIG. 6 is a morphology of a carbon fiber reinforced silicon carbide composite of example 2; wherein (a) and (b) are morphologies of the material at different magnifications.
Fig. 7 is a composition of the carbon fiber reinforced silicon carbide composite of example 2.
Fig. 8 is a stress-displacement curve of the carbon fiber reinforced silicon carbide composite of example 2.
Detailed Description
For a further understanding of the present invention, the present invention is described below with reference to the following examples, which are merely illustrative of the features and advantages of the present invention, and are not intended to limit the claims of the present invention.
The invention takes phenolic resin as a carbon source, adds glycol and curing agent with proper proportion, impregnates precursor solution formed by the phenolic resin, the curing agent and the curing agent into carbon and ceramic fiber preformed body by an impregnation method, obtains an infiltration preformed body after curing and carbonization, and can prepare the high-density and high-strength fiber reinforced SiC ceramic matrix composite material after siliconizing.
The method specifically comprises the steps of immersing a precursor solution consisting of phenolic resin, glycol and a curing agent in a specific proportion into a fiber preform, and carrying out high-pressure auxiliary phase separation, high-temperature curing and carbonization to obtain a porous carbon-based infiltration preform with a uniform nano-pore structure (40-nm) and proper porosity (45-58%). Siliconizing at a lower temperature of 1450-1550 ℃ and preserving heat for 1-2 hours, so that silicon-carbon reaction under nearly ideal state is realized: when the reaction is completed, the porous carbon matrix is completely converted into a silicon carbide matrix, and the original pore canal is completely filled by volume expansion caused in the process, so that the silicon carbide matrix is compact, carbon residue and silicon residue are avoided, and crystal grains are fine (50-100 nm) due to morphology inheritance; meanwhile, the introduced liquid silicon is completely consumed in the reaction process, and the fiber is not etched. Because the matrix strength is high (the strength of the ceramic is inversely proportional to the 1/2 th power of the grain size), and the fiber is not damaged, the mechanical property of the prepared silicon carbide-based composite material is excellent. The bending strength of the C/SiC composite material prepared by taking the T700 12K needle punched carbon fiber preform as a reinforcement can reach 270 MPa, which is far higher than that of the composite material with the same carbon fiber preform structure prepared by the traditional reaction infiltration method. Meanwhile, the generated silicon carbide substrate is compact, no carbon residue and no silicon residue are generated, and the prepared C/SiC has excellent high-temperature ablation resistance. After the composite material is ablated for 500 s in the oxyacetylene environment with the surface temperature of 2200 ℃ for a long time, the linear ablation rate is less than 0.02 mu m/s.
Example 1
The embodiment uses PAN-based T700 carbon felt prepared by a needling process technology as a fiber preform, and the specific process steps are as follows:
1) Prepared PAN-based T700 carbon felt with the density of 0.52 g/cm 3 。
2) Placing the felt body into a chemical vapor deposition furnace to deposit pyrolytic carbon matrix, wherein the carbon source is propane, the deposition temperature is 900 ℃, the deposition time is 60 h, and the density of the carbon felt reaches 0.7 g/cm 3 。
3) Preparing a precursor solution from phenolic resin, ethylene glycol and hexamethylenetetramine according to a mass ratio of 11:14:1, and soaking a felt body into the precursor solution, and keeping the mass ratio of 2 h.
4) And (3) placing the felt body in a curing furnace for curing, and preserving heat at the temperature of 180-250 ℃ under the pressure of 4 MPa for 40-h.
5) Placing the felt body in a vacuum carbonization furnace for carbonization, wherein the process is as follows: the temperature is raised to 220 ℃ from 20 ℃ and is kept at 0.5 h, the temperature is raised to 550 ℃ from 220 ℃ and is kept at 3 h, the temperature is raised to 750 ℃ from 550 and is kept at 4 h, the temperature is raised to 1000 ℃ from 750 and is kept at 2 h, and the temperature is raised to 1200 ℃ from 1000 and is kept at 2 h.
6) Repeating the steps (3) - (5) for a plurality of times until the density of the carbon/carbon composite material reaches 1.3 g/cm 3 A porous carbon matrix having a uniform pore structure was obtained.
7) The carbon/carbon composite material is placed into a siliconizing furnace, the temperature is raised to 1500 ℃ under the pressure environment of less than 20 and Pa, the temperature is kept at 1 and h, and the liquid silicon permeates into the pores of the preform and reacts with the carbon to form a silicon carbide matrix.
The morphology of the carbon matrix of the carbon/carbon composite material prepared in the step (6) of the embodiment is shown in fig. 1. It can be seen that the prepared carbon matrix is of a three-dimensional network communication structure, and the pore diameter and the carbon skeleton size of the prepared carbon matrix are distributed in a nanoscale manner. The pore size distribution of the resulting porous carbon/carbon composite is shown in fig. 2. Wherein the nanoscale peaks correspond to pores in the carbon matrix, are mainly distributed between 10 and 80 and nm, and have a median pore diameter of 43.3 nm. And large-sized pores of about 10 μm are residual pores in a small part of the unfilled preform. The density of the C/SiC composite material prepared in the embodiment is 2.15 g/cm 3 The morphology of the silicon carbide matrix of the material is shown in figure 3, and the grain size of the formed silicon carbide matrix is tens of nanometers. Fig. 4 is a morphology of the carbon fiber reinforced silicon carbide composite of example 1. It can be seen that the light source is,the porous carbon matrix is completely converted into a dense silicon carbide matrix, and the pyrolytic carbon layer and the carbon fibers remain intact and are not etched after the reaction. Therefore, the three-point bending strength of the material is up to 271.1 MPa.
Example 2
The embodiment uses PAN-based T700 carbon felt prepared by a needling process technology as a fiber preform, and the specific process steps are as follows:
1) Prepared PAN-based T700 carbon felt with the density of 0.52 g/cm 3 。
2) Placing the felt body into a chemical vapor deposition furnace to deposit pyrolytic carbon matrix, wherein the carbon source is propane, the deposition temperature is 900 ℃, the deposition time is 50 h, and the density of the carbon felt reaches 0.65 g/cm 3 。
3) Preparing a precursor solution from phenolic resin, ethylene glycol and benzenesulfonyl chloride according to a mass ratio of 11:10:2, and soaking the felt body into the precursor solution to keep 2 h.
4) And (3) placing the felt body in a curing furnace for curing, and preserving heat at the temperature of 180-250 ℃ under the pressure of 4 MPa for 40-h.
5) Placing the felt body in a vacuum carbonization furnace for carbonization, wherein the process is as follows: the temperature is raised from 20 ℃ to 220 ℃ to keep warm by 0.5 h, the temperature is raised from 220 ℃ to 550 ℃ to keep warm by 3 h, the temperature is raised from 550 ℃ to 750 ℃ to keep warm by 4 h, the temperature is raised from 750 ℃ to 1000 ℃ to keep warm by 2 h, and the temperature is raised from 1000 ℃ to 1200 ℃ to keep warm by 2 h.
6) Repeating the steps (3) - (5) until the density of the porous carbon/carbon composite material reaches 1.3 g/cm 3 。
7) The carbon/carbon composite material is placed into a siliconizing furnace, the temperature is raised to 1500 ℃ under the pressure environment of less than 20 and Pa, the temperature is kept at 1 and h, and the liquid silicon permeates into the pores of the preform and reacts with the carbon to form a silicon carbide matrix.
8) The density of the sample was 2.10 g/cm 3 The three-point bending strength was 234.9 MPa.
The pore size distribution of the carbon/carbon composite material produced in this example is shown in fig. 5. Wherein the nanoscale peaks correspond to pores in the carbon matrix, are mainly distributed between 10 and 80 and nm, and have a median pore diameter of 44.7 and nm. The density of the C/SiC composite material prepared in the embodiment is 2.10 g/cm 3 The material is shaped under different magnificationAs the appearance is shown in fig. 6, it can be seen that the porous carbon matrix is completely converted to a dense silicon carbide matrix and that the pyrolytic carbon layer and carbon fibers remain intact and unetched after the reaction. Fig. 7 is a composition of the carbon fiber reinforced silicon carbide composite of example 2. The prepared C/SiC composite material comprises a carbon peak and a silicon carbide peak without a silicon peak, which indicates that the porous carbon matrix is converted into the silicon carbide matrix in the reaction process, and the infiltrated liquid silicon is completely consumed in the reaction process. The prepared C/SiC stress-displacement curve is shown in figure 8, the three-point bending strength of the material is 234.9 MPa, and the bending stress of the material slowly decreases along with the increase of displacement in the breaking process, so that the material is in pseudoplastic breaking rather than brittle breaking. The pseudoplastic fracture behavior also indicates that the carbon fibers in the composite are not etched.
Claims (8)
1. A method for preparing a silicon carbide-based composite material by uniformly ceramifying porous carbon is characterized by comprising the following steps: firstly preparing a porous carbon matrix with a porosity of 45-58%, and then carrying out siliconizing treatment to obtain the silicon carbide-based composite material; the method specifically comprises the following steps:
(1) Dipping treatment: immersing carbon fiber or ceramic fiber preform in precursor solution for a period of time, and taking out;
(2) High-pressure auxiliary phase separation and curing treatment: pressurizing the carbon or ceramic fiber preform soaked with the precursor solution to 1-10 MPa, quickly heating to a curing temperature, and forming a porous organic matrix with uniform pore structure in the fiber preform under the conditions of external pressure and high curing temperature, namely the fiber reinforced nano porous resin matrix composite material; wherein: the curing temperature is 120-250 ℃, and the heating rate is more than 10 ℃/min; the porous organic matrix formed in the fiber preform has a three-dimensional network skeleton structure with small pore size characteristics of < 100 nm;
(3) Carbonizing: performing high-temperature carbonization treatment on the fiber reinforced nano porous resin matrix composite material obtained in the step (2) to obtain a low-density porous carbon matrix infiltration preform; the carbonization treatment process comprises the following steps: placing the fiber reinforced nano porous resin matrix composite material obtained after the curing treatment in a vacuum carbonization furnace, and heating the vacuum carbonization furnace to 1200-1800 ℃ at a heating rate of 5-10 ℃/min;
(4) Repeating the processes of soaking, curing and carbonizing in the steps (1) - (3) for a plurality of times until a porous carbon-based infiltration preform with a required density is obtained;
(5) Siliconizing treatment: and (3) performing low-temperature fusion siliconizing treatment on the porous carbon-based infiltration preform obtained in the step (4) to obtain the fiber reinforced silicon carbide composite material.
2. The method for preparing the silicon carbide based composite material by uniformly ceramifying the porous carbon according to claim 1, wherein the method comprises the following steps of: the precursor solution is prepared by mixing and uniformly stirring phenolic resin, glycol and a curing agent according to the weight ratio of (10-15): (11-16): (1-2); in the precursor solution, the phenolic resin is common commercial grade resin or modified boron phenolic aldehyde and barium phenolic aldehyde, and the curing agent is at least one of sodium carbonate, propylene carbonate, p-toluenesulfonic acid, phosphoric acid, benzenesulfonic acid, benzenesulfonyl chloride, hexamethylenetetramine and methylol urea.
3. The method for preparing the silicon carbide based composite material by uniformly ceramifying the porous carbon according to claim 1, wherein the method comprises the following steps of: in the step (1), the carbon fiber and ceramic fiber preform may be provided with an interface layer, which is one or more of a pyrolytic carbon interface, a silicon carbide interface, or a boron nitride interface.
4. The method for preparing the silicon carbide based composite material by uniformly ceramifying the porous carbon according to claim 1, wherein the method comprises the following steps of: in the impregnation treatment of step (1): the pressure range is 0.1-9 MPa, the soaking time is 1-4 h, and the soaking treatment is finished when no obvious bubbles exist.
5. The method for preparing the silicon carbide based composite material by uniformly ceramifying the porous carbon according to claim 1, wherein the method comprises the following steps of: in the step (4), the pore size distribution range of the carbon matrix in the obtained porous carbon-based infiltration preform is 10-80 nm, and the pore size of the median pore is 40-45 nm.
6. The method for preparing the silicon carbide based composite material by uniformly ceramifying the porous carbon according to claim 1, wherein the method comprises the following steps of: in the step (5), in the siliconizing treatment process, the siliconizing temperature is 1450-1550 ℃, the heat preservation time is 1-2 h, the grain size of the used silicon powder is 10 mu m-2 mm, and the pressure in the infiltration process is less than 20 Pa.
7. The method for preparing the silicon carbide based composite material by uniformly ceramifying the porous carbon according to claim 1, wherein the method comprises the following steps of: in the step (4), the porosity of the porous carbon matrix obtained after carbonization treatment is obtained by calculating the matching relation between the porosity P of the porous carbon matrix and the volume expansion rate under the ideal condition that the porous carbon generates compact silicon carbide after reaction: p=1-V m C/V m SiC, wherein: v (V) m C is the molar volume of the porous carbon matrix, V m SiC is the dense silicon carbide matrix molar volume.
8. The method for preparing the silicon carbide based composite material by uniformly ceramifying the porous carbon according to claim 1, wherein the method comprises the following steps of: the silicon carbide substrate obtained in the step (5) is compact, no carbon residue and no silicon residue exist in the silicon carbide substrate, and the grain size of the silicon carbide is 50-100 nm; and after the reaction, the fibers in the composite material are not etched.
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