CN106588060B - A kind of highly dense silicon carbide ceramic matrix composite material and its preparation method - Google Patents

Abstract

The present invention relates to a kind of high-densit carbon/silicon carbide ceramic matrix composites and preparation method thereof, comprising: using in the precursor liquid dipping fiber preform containing high carbon output rate resin, low Residual carbon organic polymer, fiber/C infiltration precast body is obtained after cracking；And the Si of the melting or Si of melting is penetrated into progress infiltration in the fiber/C infiltration precast body with the alloy of metal and is reacted, obtain the carbon/silicon carbide ceramic matrix composite.The present invention changes the structure that resin in infiltration precast body cracks the carbon to be formed by adding low Residual carbon polymer, contact and reaction of the silicon with carbon when promoting to react infiltration, metal is in the generation that disperse shape is distributed and effectively prevents blocky residual carbon and blocky residual metal in the base after infiltration, to significantly improve the mechanical property and thermal conductivity of composite material.

Description

A kind of highly dense silicon carbide ceramic matrix composite material and its preparation method

technical field

The invention relates to a high-density silicon carbide ceramic matrix composite material and a preparation method thereof, in particular to a silicon carbide ceramic matrix composite material with high density and high thermal conductivity and a preparation method of reaction infiltration.

Background technique

With the development of high-tech fields such as aviation, aerospace, and energy, more and more components are in extreme service environments, so there is an urgent need for high-performance materials. For example, aero-engines and gas turbines urgently need materials suitable for the coupling environment of force-heat-oxidation, and high-resolution remote sensing satellites urgently need materials that are lightweight, long-lived, and suitable for space service environments. The temperature limit of nickel-based superalloys currently used in aero-engines is about 1100°C, and the density of nickel-based alloys is relatively high, which greatly limits the further improvement of engine performance; Invar alloys used in remote sensing satellite support structures And resin-based composite materials can no longer meet the requirements of large-aperture long-focus cameras. Fiber-reinforced silicon carbide ceramic matrix composites have low density, high temperature resistance, excellent mechanical properties, and strong designability. They are considered to be a new generation of structural materials that can replace or partially replace traditional materials in high-tech fields.

The preparation methods of silicon carbide ceramic matrix composites mainly include chemical vapor deposition (CVI), organic precursor impregnation-pyrolysis (PIP) and reactive infiltration (RMI). CVI and PIP methods can obtain silicon carbide ceramic matrix composites at lower temperatures, which is beneficial to avoid damage to fibers at high temperatures, but the material preparation cycle is long, and the prepared composites have many defects such as pores and cracks. Performance has certain limitations. Among several preparation techniques of ceramic matrix composites, the RMI method is the only method that can obtain highly dense materials in a short time. In the preparation process, Si or its alloys are first melted, and the metal melt penetrates into the porous fiber/C under the action of capillary force, and chemically reacts with the matrix C to form a ceramic matrix including silicon carbide. However, since the porous fiber/C material is mostly prepared by phenolic resin impregnation-pyrolysis process, the generated C particle size is large, and the distribution of crack and pore size is uneven. In addition, due to insufficient contact between molten metal and bulk carbon source during RMI, there is a large amount of unreacted residual carbon and metal in the final SiC ceramic matrix composites obtained. The document "Jiping Wang, Min Lin, Zhuo Xu, et al. Microstructure and mechanical properties of C/C–SiC composites fabricated by a rapid processing method [J]. Journal of the European Ceramic Society, (2009) 3091-3097." uses RMI The process densifies the C _f /C preforms with different pores, and quickly obtains dense C _f /C-SiC composites, but there is a concentrated distribution of residual Si between and within the fiber bundles, which affects the mechanical properties of the composites. The carbon source used in this method is deposited using the CVI process. The reason for the concentrated distribution of residual Si is that CVI carbon is a layered structure, and Si can only react with part of the carbon, resulting in a concentrated distribution of residual silicon. Document "Honglei Wang, Xingui Zhou, Jinshan Yu, et al.Fabrication of SiC _f /SiCcomposites by chemical vapor infiltration and vapor silicon infiltration[J].Materials Letters 64(2010)1691-1693." Prepared by vapor phase silicon infiltration A dense SiC _f /SiC composite material is obtained, but there are large areas of residual carbon and silicon concentrated in the composite material. The carbon source used in this method is deposited using the CVI process. The reason for the concentrated distribution of residual Si is that CVI carbon is a layered structure, and Si can only react with part of the carbon, so that there is a concentrated distribution of residual silicon. The improvement of mechanical properties and thermal conductivity is extremely unfavorable.

Contents of the invention

The present invention aims at the problem of large-size residual Si or alloy and large-size residual carbon in the matrix due to insufficient reaction between Si or Si and alloys of other metals and C in the traditional RMI preparation process of silicon carbide ceramic matrix composite materials, and provides an improvement Fiber/C infiltration preform structure construction infiltration reaction preparation method.

In one aspect, the present invention provides a method for preparing a highly dense silicon carbide ceramic matrix composite material, comprising:

Impregnating the fiber preform with a precursor liquid containing a resin with a high carbon yield and an organic polymer with a low carbon residue rate, and cracking to obtain a fiber/C infiltration preform; and

Infiltrating molten Si or an alloy of molten Si and metal into the fiber/C infiltration preform to carry out an infiltration reaction to obtain the silicon carbide ceramic matrix composite material.

The present invention starts from the source, increases the contact area between the metal melt and C, and promotes the kinetics of the infiltration reaction by adjusting the structure of the fiber-infiltration prefabricated body. Specifically, high carbon yield resins (resins with carbon yields higher than 60%) are used as carbon sources, and organic polymers with low carbon residue rates (or low carbon residue rate polymers for short) that have good compatibility with resins, specifically refer to An organic polymer with a residual carbon rate lower than 15%) is used as a carbon matrix structure regulator, and the homogeneous blend of the two is impregnated and solidified inside the fiber preform. The present invention utilizes the curing polymerization reaction of the high-carbon-yield resin itself to induce the phase separation of the high-carbon-yield resin/carbon matrix structure regulator, and promotes the two (high-carbon-yield resin and low-carbon-residue polymer) to form a network interpenetrating structure. Combined with the low-carbon residual characteristics of the regulator in the further high-temperature pyrolytic carbonization process, a carbon matrix structure suitable for infiltration reaction is constructed inside the fiber preform, and the particle size of pyrolytic carbon in the carbon matrix is significantly reduced to break through the existing The limitation of the preparation method realizes the full reaction of metal and C in the reaction infiltration process, avoids the residue of bulk carbon and bulk metal, and lays a good foundation for further improving the comprehensive performance of composite materials and practical applications.

Preferably, the high carbon yield resin is at least one of furfuryl alcohol resin, pitch resin, benzoxazine resin, and phenolic resin, preferably a mixture of furfuryl alcohol resin and phenolic resin. Preferably, the low carbon yield organic polymer is at least one of polyethylene glycol, epoxy resin, and microcrystalline cellulose, preferably polyethylene glycol.

Preferably, in the precursor liquid, the mass ratio of the high carbon yield resin to the low carbon residue organic polymer is (0.05-8):1, preferably (2-4):1.

Also, preferably, the organic polymer with low carbon residue rate is polyethylene glycol.

Preferably, the solvent is at least one of ethanol, acetone and formaldehyde.

Preferably, the mass ratio of the low carbon residue rate organic polymer to the solvent is (0.1-2):1, preferably (0.25-0.5):1.

Preferably, the form of the fiber preform includes carbon fiber, silicon carbide fiber or a two-dimensional stitched weaving structure mixed with carbon fiber and silicon carbide fiber, a three-dimensional needle-punched weaving structure, a three-dimensional four-way weaving structure, a three-dimensional five-way weaving structure, a one-dimensional structure, Two-dimensional laminated structure, but not limited to the above-mentioned fiber arrangement structure.

Preferably, before the impregnation, at least one of SiC ceramic matrix, cracked carbon interface and BN interface is prepared in the fiber preform. The SiC ceramic matrix is prepared in the fiber preform, and the SiC ceramic matrix is evenly distributed inside and/or on the surface of the fiber in the fiber preform, mainly to reduce the loss of the fiber during Si infiltration, so as to protect the fiber. In addition, the cracked carbon interface and BN interface prepared in the preform not only protect the fibers, but also transmit loads, which is beneficial to the improvement of the mechanical properties of the material.

Preferably, the impregnation process parameters include: vacuum degree -0.08MPa--0.10MPa; curing reaction temperature 100-150°C; curing reaction time 1-3 hours.

Preferably, the cracking is carried out at 850-1000° C. for 20-40 minutes in an inert atmosphere.

Preferably, the inert atmosphere is an argon atmosphere.

Also, preferably, the flow rate of the inert atmosphere is controlled to 3-8 min/L.

Preferably, the infiltration reaction is carried out at 1250-1600° C. for 0.5-2 hours, and the degree of vacuum is <10 Pa.

In another aspect, the present invention provides a silicon carbide ceramic matrix composite material, the porosity of the silicon carbide ceramic matrix composite material is 1-5%, the thermal conductivity is 25-40 W/m·K, and the bending strength is 300 ~500MPa.

Beneficial effects of the present invention:

By adding a polymer with a low carbon residue rate, the structure of carbon formed by resin cracking in the infiltration preform is changed, and the contact and reaction of silicon and carbon are promoted during reactive infiltration. After infiltration, the metal is dispersed in the matrix and effectively avoided. The generation of massive residual carbon and massive residual metal can significantly improve the mechanical properties and thermal conductivity of composite materials.

Description of drawings

Fig. 1 is the process flow diagram of preparing high-density silicon carbide ceramic matrix composite material of the present invention;

Fig. 2 is the SEM photo of the polished section of the C _f /C infiltration preform prepared in Example 1;

Fig. 3 is the pore size distribution diagram of the C _f /C infiltration preform prepared in Example 1;

Fig. 4 is the SEM photo of the polished section of the C _f /SiC composite material prepared in Example 1;

Fig. 5 is the X-ray diffraction spectrum of the polished section of the C _f /SiC composite material prepared in Example 1;

Fig. 6 is the SEM photo of the polished section of the C _f /C infiltration preform prepared in Comparative Example 1;

Fig. 7 is the pore size distribution diagram of the C _f /C infiltration preform prepared in Comparative Example 1;

FIG. 8 is an SEM photo of the polished cross-section of the C _f /SiC composite material prepared in Comparative Example 1. FIG.

Detailed ways

The present invention will be further described below through the following embodiments. It should be understood that the following embodiments are only used to illustrate the present invention, not to limit the present invention.

In the present invention, the resin with high carbon yield is used as the carbon source, and the polymer with low residual carbon rate is used as the carbon matrix structure regulator. The precursor is introduced into the fiber prefabricated body through vacuum impregnation, and the fiber/C infiltration prefabrication is obtained by heat treatment under certain conditions. body, and then the ceramic matrix including the SiC matrix is generated in situ by the reaction infiltration method to obtain a highly dense silicon carbide ceramic matrix composite material. Specifically, resins with high carbon yields are used as carbon sources and polymers with low residual carbon ratios are used as carbon matrix structure regulators. Resin C is introduced into the fiber prefabricated body by impregnation-pyrolysis process, and then Si or its alloys are introduced into the in-situ reaction by RMI method. A highly dense silicon carbide ceramic matrix composite material is obtained.

The preparation method of the high-density silicon carbide ceramic matrix composite material provided by the present invention is exemplarily described below.

Pretreatment of fiber preforms. A small amount of ceramic matrix is prepared in the fiber preform to protect the fibers (the ceramic matrix may be 0.5-4 times the mass of the fiber preform). The ceramic matrix is only a SiC ceramic matrix, but it can be prepared in a preform such as cracked carbon interface, BN interface, etc. The ceramic matrix can be at least one of a SiC ceramic matrix, a cracked carbon interface, and a BN interface. The method for preparing the SiC ceramic matrix includes: preparing the SiC ceramic matrix by a chemical vapor deposition infiltration method, using trichloromethylsilane as a gas source, hydrogen as a carrier gas, and depositing in a tube furnace at 1000° C. for 100-200 hours. . The method for forming the cracked carbon interface includes: using methane as a gas source, depositing in a tube furnace at 1000° C. for 3-6 hours. The method for forming the BN interface includes: using boron trichloride ammonia gas as a gas source, depositing in a tube furnace at 1000° C. for 3-6 hours.

Preparation of precursor fluids. After dispersing high-carbon-yield resins and low-carbon-residue organic polymers in solvents (such as ethanol, acetone, formaldehyde, etc.), a constant-temperature water bath is ultrasonically obtained to obtain a precursor liquid. In one example, a low carbon residue polymer (LCP) is dissolved to obtain a low carbon residue polymer solution, and then a certain amount of high carbon yield resin (HCR) is added, and a constant temperature water bath is ultrasonically obtained to obtain a precursor solution. However, it should be understood that the order of adding the low carbon residue polymer (LCP) and the high carbon yield resin (HCR) is not limited to this (in theory, as long as the LCP and HCR can be dissolved in the solvent, it is enough, but in the actual operation process, first Adding HCR after adding LCP is easier to dissolve in the solvent).

The above-mentioned high carbon yield resins include but are not limited to furfuryl alcohol resins, pitch resins, benzoxazine resins, bismaleimide resins, phenolic resins or their mixed resins, preferably furfuryl alcohol resins, phenolic resins and their mixed resins. Polymers with low residual carbon ratio include but are not limited to polyethylene glycol, epoxy resin, microcrystalline cellulose, preferably polyethylene glycol. The mass ratio of the high carbon yield resin to the low carbon residue polymer may be (0.05-8):1, preferably (2-4):1. The proportion of organic polymer with low carbon residue rate is too low to have the effect of regulating pores. The mass ratio of the low carbon residue polymer to the solvent may be (0.1-2):1, preferably (0.25-0.5):1.

The precursor is introduced into the fiber preform or the pretreated fiber preform by vacuum impregnation, and solidified to obtain the fiber/HCR-LCP molded body. Wherein, the vacuum degree of vacuum impregnation is -0.08MPa～-0.10MPa. The curing reaction temperature may be 100-150°C. The curing reaction time can be 1-3 hours. The curing polymerization reaction of the resin is used to induce the phase separation of the resin/regulator, and promote the formation of a network interpenetrating structure between the two (resin with high carbon yield and polymer with low carbon residue rate).

The above-mentioned fiber prefabricated forms include carbon fiber, silicon carbide fiber or a two-dimensional stitched weaving structure mixed with carbon fiber and silicon carbide fiber, a three-dimensional needle-punched weaving structure, a three-dimensional four-way weaving structure, a three-dimensional five-way weaving structure, a one-dimensional structure, and a two-dimensional laminated structure. Layer structure, but not limited to the above-mentioned fiber arrangement structure.

The fiber/HCR-LCP formed body is lysed under an inert atmosphere (for example, argon, etc.). Wherein the cracking condition is 20-40 minutes at 850-1000°C. Control the flow of inert gas argon to 3-8min/L.

The steps of vacuum impregnation and cracking under inert atmosphere are repeated 1-5 times to obtain a fiber/C infiltration preform. Wherein, the pore size distribution of the obtained fiber/C infiltration preform can be 0.1-10 μm, the porosity is 20-40%, and the median pore size is 0.5-5 μm, preferably 0.8-1.2 μm.

Infiltrate molten Si or alloys of molten Si and other metals (for example, Y, Yb, Al, etc.) into the fiber/C infiltration preform for infiltration reaction to generate a ceramic matrix including SiC in situ, and obtain the described Silicon carbide ceramic matrix composites. The conditions for the infiltration reaction can be 1250-1600° C. for 0.5-2 hours, and the vacuum degree is better than 10 Pa.

Taking furfuryl alcohol resin, phenolic resin, polyethylene glycol, and Si system as an example, the process flow is shown in Figure 1: (1) Preform treatment: prepare a certain amount of SiC ceramic matrix in the carbon fiber preform, Fibers are protected. (2) Preparation of precursor body fluid: Dissolve polyethylene glycol (PEG) in ethanol to obtain a polyethylene glycol solution, add a certain amount of furfuryl alcohol resin (FFR) and phenolic resin (PFR), and obtain a precursor body fluid by ultrasonication in a water bath. Wherein the mass ratio of furfuryl alcohol resin and phenolic resin is (0.1～9): 1, preferably (1～3): 1; The mass ratio of furfuryl alcohol resin and polyethylene glycol is (0.1～4): 1, preferably (1.5～2.5 ):1; the mass ratio of polyethylene glycol and ethanol is (0.1～2):1, preferably (0.25～0.5):1. (3) Vacuum impregnation curing: introduce the precursor solution in (2) into the fiber preform in (1) by vacuum impregnation (-0.08MPa～-0.10MPa vacuum degree), and keep warm at 100～150℃ for 6～ Curing was complete in 10 hours to give C _f /FFR-PFR-PEG. (4) Cracking: put the _Cf /FFR-PFR in (3) into a cracking furnace for cracking (cracking condition is 850～1000° C. for 20～40 minutes), and maintain an argon atmosphere (for example, the Ar gas flow rate is 3～8min/L), after cracking, a C _f /C infiltration preform is obtained. The pore size distribution of the obtained C _f /C infiltration preform is 0.1～10μm, the porosity is 20～40%, and the median pore diameter is 0.5～5μm. (5) Steps (3) (4) are repeated 1-5 times to obtain C _f /C infiltrated preforms with different porosities. (6) Reactive infiltration: Under vacuum, under certain temperature conditions, molten Si is infiltrated into C _f /C to react with C in situ to form a SiC matrix, and the preparation of the material is completed. Wherein, the Si infiltration condition is 1380-1600° C. for 0.5-2 hours.

In the example above, the main reactions involved are:

Cleavage reaction: FFR+PFR→C;

Infiltration reaction: Si+C→SiC.

The invention can promote the sufficient contact and reaction of metal and carbon during reaction infiltration, and there is no massive residual metal in the silicon carbide ceramic matrix composite material matrix after infiltration, and the ceramic matrix particles rich in metal are fine and dispersed, without large The concentrated distribution of block carbon significantly improves the mechanical properties and thermal conductivity of the material. The porosity of the silicon carbide ceramic matrix composite material may be 1-5%, the thermal conductivity may be 25-40 W/m·K, and the bending strength may be 300-500 MPa.

Examples are given below to describe the present invention in detail. It should also be understood that the following examples are only used to further illustrate the present invention, and should not be construed as limiting the protection scope of the present invention. Some non-essential improvements and adjustments made by those skilled in the art according to the above contents of the present invention all belong to the present invention scope of protection. The specific process parameters and the like in the following examples are only examples of suitable ranges, that is, those skilled in the art can make a selection within a suitable range through the description herein, and are not limited to the specific values exemplified below.

Example 1

(1) Preform treatment: 800 g of SiC ceramic matrix was prepared from 800 g of carbon fiber preform. The specific method can be to use trichloromethylsilane as the gas source, hydrogen as the carrier gas, and deposit the fiber preform in a tube furnace at 1000° C. for 100 hours. ;

(2) Precursor preparation: 100g polyethylene glycol (PEG) was dissolved in 400g ethanol; 200g furfuryl alcohol resin (FFR) and 200g phenolic resin (PFR) were added to the above solution, and the precursor was obtained by ultrasonication in a water bath at 50°C for 6 hours body fluid;

(3) Vacuum impregnation: under the vacuum condition of -0.08MPa～-0.10MPa, the precursor liquid in (2) is introduced into the C _f preform in (1), and it is cured at 120°C for 2 hours to obtain C _f /FFR -PFR-PEG;

(4) Cracking: Put the C _f /FFR-PFR-PEG in (3) into a cracking furnace for cracking, keep it at 1000°C for 0.5 hours, and maintain an Ar atmosphere of 5 L/min during the cracking, and obtain C _f /C melt seepage prefabricated body;

(5) Reaction infiltration: Under the infiltration conditions of vacuum and 1500°C for 1 hour, molten Si was infiltrated into C _f /C and reacted with C in situ to form a SiC matrix to complete the preparation of the material.

The SEM photo of the polished section of the C _f /C infiltrated preform prepared in this example is shown in Figure 2. It can be seen that the resin carbon is porous and distributed among the fiber bundles. The pore size distribution of the C _f /C infiltrated preform prepared in this example is shown in FIG. 3 , and the pore size distribution is mostly between 0.3 and 5 μm. The SEM photo of the polished cross-section of the C _f /SiC composite material prepared in this example is shown in Figure 4, where the dot-like silicon-rich ceramic matrix is diffusely distributed and there is no residual carbon. The X-ray diffraction pattern of the polished section of the prepared C _f /SiC composite material is shown in Figure 5, indicating that the matrix of the composite material is dominated by two phases of silicon and silicon carbide.

The C _f /C infiltration preform prepared in this example passed the Autopore IV 9500V 1.09 mercury intrusion test, and the median pore diameter was 1.78 μm; the prepared C _f /SiC composite material passed the Archimedes drainage test, and the porosity The thermal conductivity measured by NETZSCHLFA427 laser thermal conductivity meter is 30W/m·K, and the bending strength is 344MPa after testing by CIMACH DDL20 electronic universal testing machine.

Example 2

Similar to the steps in Example 1, the difference is that (3) (4) steps are repeated once;

The C _f /C infiltration preform prepared in this example passed the Autopore IV 9500V 1.09 mercury intrusion test, and the median pore diameter was 1.16 μm; the prepared C _f /SiC composite material passed the Archimedes drainage test, and the porosity The thermal conductivity measured by NETZSCHLFA427 laser thermal conductivity meter is 33W/m·K, and the bending strength is 398MPa after being tested by CIMACH DDL20 electronic universal testing machine.

Example 3

Similar to the steps in Example 1, the difference is that (3) (4) steps are repeated twice;

The C _f /C infiltration preform prepared in this example passed the Autopore IV 9500V 1.09 mercury intrusion test, and the median pore diameter was 0.92 μm; the prepared C _f /SiC composite material passed the Archimedes drainage test, and the porosity The thermal conductivity measured by NETZSCHLFA427 laser thermal conductivity meter is 38W/m·K, and the bending strength is 460MPa after CIMACH DDL20 electronic universal testing machine test.

Example 4 (the mass ratio of the high carbon yield resin and the low carbon residue rate organic polymer is 2:1)

Similar to the steps in Example 1, the difference is: 100g polyethylene glycol is added to 400g ethanol; 200g furfuryl alcohol resin (FFR) is added to the above solution, the above solution is added, and the precursor is obtained by ultrasonication in a water bath at 50°C for 6 hours solution;

The C _f /C infiltration preform prepared in this example passed the Autopore IV 9500V 1.09 mercury intrusion test, and the median pore diameter was 2.58 μm; the prepared C _f /SiC composite material passed the Archimedes drainage test, and the porosity The thermal conductivity measured by NETZSCHLFA427 laser thermal conductivity meter is 35W/m·K, and the bending strength is 380MPa after testing by CIMACH DDL20 electronic universal testing machine.

Comparative example 1 (precursor solution does not contain low carbon residue rate polymer)

Similar to the steps in Example 1, the difference is (2) Precursor preparation: Mix 200g furfuryl alcohol resin and 200g phenolic resin to form a furfuryl alcohol phenolic mixed resin; add 400g ethanol and ultrasonicate for 2 hours to obtain a precursor.

The SEM photo of the polished section of the C _f /C infiltration preform prepared in this comparative example is shown in Figure 6. It can be seen from the figure that when no carbon matrix structure regulator is added, the cracked resin carbon is in the form of large blocks distributed among fiber bundles. Figure 7 is the pore size distribution diagram of the C _f /C infiltration preform prepared in this comparative example. It can be seen from the figure that the pore size of the C _f /C infiltration preform is between 10 and 30 μm when no carbon matrix structure regulator is added. between. The SEM photo of the polished section of the C _f /SiC composite material prepared in this comparative example is shown in Figure 8. It can be seen from the figure that when no carbon matrix structure regulator is added, there are unreacted large pieces of carbon in the matrix. And silicon concentrated distribution.

Claims (11)

1. A method for preparing a high-density silicon carbide ceramic matrix composite material, characterized in that it comprises: The fiber preform is impregnated with a precursor liquid containing a resin with a high carbon yield and an organic polymer with a low residual carbon rate, and the fiber/C infiltration preform is obtained after cracking. The resin with a high carbon yield is furfuryl alcohol resin, asphalt resin, and benzoxan At least one of oxazine resin and phenolic resin, the low carbon residue rate organic polymer is at least one of polyethylene glycol, epoxy resin, and microcrystalline cellulose, and the high carbon yield resin and The mass ratio of organic polymer with low carbon residue rate is (0.05-8):1; and Infiltrating molten Si or an alloy of molten Si and metal into the fiber/C infiltration preform to perform an infiltration reaction to obtain the silicon carbide ceramic matrix composite material; The porosity of the silicon carbide ceramic matrix composite material is 1-5%, the thermal conductivity is 25-40W/m·K, and the bending strength is 300-500MPa. 2. preparation method according to claim 1, is characterized in that, described high carbon yield resin is the mixture of furfuryl alcohol resin and phenolic resin. 3. The preparation method according to claim 1, characterized in that, the low carbon residue rate organic polymer is polyethylene glycol. 4 . The preparation method according to claim 1 , wherein, in the precursor liquid, the mass ratio of the high carbon yield resin to the low carbon residue organic polymer is (2-4):1. 5. The preparation method according to claim 1, characterized in that, the solvent used for the precursor body fluid is at least one of ethanol, acetone, and formaldehyde. 6 . The preparation method according to claim 1 , wherein the mass ratio of the organic polymer with low carbon residue rate to the solvent is (0.1-2):1. 7 . The preparation method according to claim 6 , wherein the mass ratio of the organic polymer with low carbon residue rate to the solvent is (0.25-0.5):1. 8. The preparation method according to claim 1, characterized in that the impregnation process parameters include: vacuum degree -0.08MPa～-0.10MPa; curing reaction temperature is 100-150°C; curing reaction time is 1 ~3 hours. 9. The preparation method according to claim 1, characterized in that, before the impregnation, at least one of a SiC ceramic matrix, a cracked carbon interface, and a BN interface is prepared in the fiber preform. 10. The preparation method according to claim 1, characterized in that, the cracking is in an inert atmosphere at 850-1000° C. for 20-40 minutes. 11. The preparation method according to any one of claims 1-10, characterized in that the infiltration reaction is at 1250-1600° C. for 0.5-2 hours, and the vacuum degree is <10 Pa.