CN110028330A - A kind of ceramic matric composite and preparation method thereof - Google Patents

Abstract

The present invention proposes a kind of ceramic matric composite and preparation method thereof, and the carbon fiber precast body is impregnated in hafnium tantalum silicon ternary complex phase ceramic precursor solution and is made by solidification, cracking using carbon fiber precast body as skeleton by preparation-obtained composite material.Preparation method prepares pyrolysis carbon boundary layer using chemical vapor infiltration in carbon fiber precast body, carries out matrix densification processing by hafnium tantalum silicon ternary complex phase ceramic polymer infiltration and pyrolysis method, finally carries out sealing pores using chemical vapor infiltration.The method of the present invention technical process is simple, the lead time is short, prepared each constituent element of ultra-temperature ceramic-based composite material matrix is evenly distributed, with superhigh temperature resistant, anti-oxidant, ablation resistance, the high temperature thermal structure material that can be used as hypersonic aircraft and rocket propulsion system, has broad application prospects.

Description

A kind of ceramic matrix composite material and preparation method thereof

technical field

The invention relates to a ceramic matrix composite material and a preparation method thereof, in particular to a carbon/hafnium tantalum solid solution-silicon carbide ceramic matrix composite material and a preparation method thereof, belonging to the technical field of composite materials.

Background technique

Carbon fiber toughened silicon carbide ceramic matrix composites (C _f /SiC composites) are high-performance thermal structural materials. It overcomes the Achilles heel of the brittleness of single-phase ceramic materials, and has excellent properties such as low density, high temperature resistance, high strength, oxidation resistance and ablation resistance. It can be used as aerospace structural materials, brake materials, and has been used in hypersonic aircraft wings. applied to the rudder. However, long-term research has shown that the long-term anti-oxidation temperature of traditional C _f /SiC composites does not exceed 1650 °C. When the Mach number of a hypersonic vehicle exceeds 6, its high-temperature structural parts such as ends, leading edges, engine combustion chambers, engine nozzles, etc. need to withstand high temperature, temperature shock, strong oxidation and airflow scouring environment, and the temperature exceeds 2000℃. In order to improve the high temperature oxidation resistance and ablation resistance of C _f /SiC composites, it is an effective method to introduce ultra-high temperature ceramic phase into its matrix to prepare ultra-high temperature ceramic matrix composites containing multi-component matrix.

Zirconium carbide is a kind of high melting point carbide. Zirconium carbide is introduced into the matrix of C _f /SiC composite material to prepare C _f /SiC-ZrC composite material, which has good oxidation resistance and greatly improved temperature resistance. . For example, patent applications CN201410431045.4, CN201410348051.3, CN201310178206.9, etc. have respectively prepared high temperature and oxidation resistant C _f /SiC-ZrC composite materials by hot pressing sintering method, precursor impregnation cracking method and reactive infiltration method, but ZrC ZrO _{2 is formed by oxidation in a high temperature oxidizing atmosphere, and the bond strength between ZrO 2 and} the matrix is low, which leads to the decrease of the mechanical properties of the composite material. Therefore, in the oxidative service environment above 2500 °C, the comprehensive properties of C _f /SiC-ZrC composites are poor, which limits the application of C _f /SiC-ZrC composites.

The hafnium-tantalum solid solution has an ultra-high melting point, such as the melting point of Ta ₄ HfC ₅ (a hafnium-tantalum solid solution) exceeding 4000°C, and has good oxidation resistance. However, there has been no report on the hafnium-tantalum solid solution modified carbon/silicon carbide and other composite materials. The reason may be that, based on the characteristics of the hafnium-tantalum solid solution, there is no suitable process to uniformly disperse the hafnium-tantalum solid solution in silicon carbide. . Therefore, based on the above background, there is an urgent need for a ceramic matrix composite material with high temperature resistance and excellent mechanical properties at the same time.

SUMMARY OF THE INVENTION

The following presents a brief summary of the present invention in order to provide a basic understanding of certain aspects of the invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to identify key or essential parts of the invention nor to limit the scope of the invention. Its sole purpose is to present some concepts in a simplified form as a prelude to the more detailed description that is discussed later.

The purpose of the present invention is to overcome the deficiencies in the prior art, and to provide a ceramic matrix composite material and a preparation method thereof.

The technical solution of the present invention is:

In one aspect, the present invention provides a ceramic matrix composite material. The composite material uses a carbon fiber preform as a skeleton, and the carbon fiber preform is immersed in a hafnium-tantalum-silicon ternary composite ceramic precursor solution and undergoes solidification and cracking. be made of.

Further, the hafnium-tantalum-silicon ternary composite ceramic precursor solution comprises a hafnium-tantalum coordination copolymer resin, polycarbosilane and a carbon source precursor.

Further, in the hafnium-tantalum-silicon ternary composite ceramic precursor solution, the content of the carbon source precursor is higher than that of the hafnium-tantalum coordination copolymer resin.

Further, the hafnium-tantalum coordination copolymer resin is obtained by using hafnium tetrachloride and tantalum pentachloride as raw materials, and adding a certain amount of ligands through a polymerization reaction.

Further, the pyrolysis temperature is 1600-1800°C.

On the other hand, the present invention also provides a preparation method of a ceramic matrix composite material, comprising the following steps:

Step 1. Preparation of composite material preform,

Densifying the carbon fiber fabric to obtain a composite material preform with a density of 1.10-1.25 g/cm ³ ;

This step is known in the art, and chemical vapor deposition process or other densification methods can be used, as long as the density of the obtained composite material reinforcement can be guaranteed to be within the above range; the reason is: if the density is too large, the pores are too small, and the subsequent The efficiency of the PIP process is low. If the density is too small, the pyrolytic carbon interface layer is too thin, and the carbon fiber is easily damaged;

The present invention adopts a vapor deposition process to prepare a composite material preform (other processes can be selected according to actual needs): the carbon fiber fabric is placed in a vapor deposition furnace, and a chemical vapor deposition process is used to deposit a pyrolytic carbon interface layer on the surface of the preform. The deposition time is preferably 300 to 500 hours;

The carbon fiber fabric used in the present invention has no special requirements, for example, it can be a needle-punched structure, a fine-knitted puncture structure or a sutured structure, and its purpose is to serve as the skeleton of the carbon/hafnium-tantalum solid solution-silicon carbide composite material, and play the role of strengthening and toughening;

Step 2, cross-linking and curing of composite material preform,

The composite material preform described in step 1 is immersed in the precursor solution of the hafnium-tantalum-silicon ternary composite ceramic precursor using vacuum pressure, and is subjected to pressure cross-linking and curing;

In this step, the process conditions for vacuum pressure impregnation and curing are preferably as follows: first, immersion in an environment with a vacuum degree of 5-200KPa for 1-2 hours, and then immersion in a pressure tank with a pressure of 2-6MPa for 2-4 hours, so that The precursor is completely immersed in the preform, and finally cross-linked and cured in a pressure tank with a pressure of 8 to 20 MPa for 8 to 15 hours. The material obtained under this process has better curing effect and higher density after curing and cracking;

In this step, the hafnium-tantalum-silicon ternary composite ceramic precursor solution comprises hafnium-tantalum coordination copolymer resin, polycarbosilane and carbon source precursor;

Further, the hafnium-tantalum coordination copolymer resin is obtained by using hafnium tetrachloride and tantalum pentachloride as raw materials, and adding a certain amount of ligands through a polymerization reaction;

Preferably, the preparation method of the hafnium-tantalum coordination copolymer resin is:

In parts by weight, 1 part of hafnium tetrachloride, 1 to 4 parts of tantalum pentachloride and 5 parts of n-propanol are mixed, placed in an ice-water bath at 0°C, and 3 to 5 drops of catalyst are added dropwise to react for 2 to 4 hours. Then, 5 parts of ligands are added, and the polymerization reaction is carried out at 70-90° C. for 3-5 hours. Atmospheric distillation was carried out for 5 hours to remove excess solvent to obtain a hafnium-tantalum coordination copolymer resin.

Wherein, the catalyst is an amine, preferably diethylamine, which has the advantage of accelerating the reaction speed of hafnium tetrachloride, tantalum pentachloride and n-propanol;

The ligand is an organic small molecule, preferably acetylacetone, which has the advantage of easily forming a coordination polymer with metal hafnium and tantalum, so that hafnium and tantalum can be connected to the same polymer molecular chain.

Further, in the hafnium-tantalum-silicon ternary composite ceramic precursor solution, the content of the carbon source precursor is higher than the content of the hafnium-tantalum coordination copolymer resin, and preferably the carbon source precursor is higher than the hafnium-tantalum coordination copolymer resin. The advantage of this configuration is that it is easy to form a hafnium-tantalum solid solution during cracking, and the reaction is relatively complete. If the carbon source precursor is too small, ultra-high temperature ceramics such as hafnium carbide and tantalum carbide will be formed. If it is too much, there will be more free carbon, which will reduce the high temperature ablation resistance of the composite material;

Further, the types of the carbon source precursors are not particularly limited, and materials that can provide carbon sources commonly used in the preparation of ceramic materials in the art can be used. In the present invention, it is preferably a phenolic resin, more preferably an allyl group. Phenolic Resin;

Further, preferably, the preparation method of the hafnium tantalum silicon ternary composite ceramic precursor solution is:

In parts by weight, 1 to 5 parts of hafnium-tantalum coordination copolymer resin, 1 part of polycarbosilane and 2 to 6 parts of carbon source precursor are added to 4 to 5 parts of solvent, mechanically stirred for 5 to 8 hours, Leave for 5 to 10 hours to obtain a uniform hafnium-tantalum-silicon ternary composite ceramic precursor solution; wherein, the solvents are alcohols and xylene, which have the advantage of simultaneously dissolving hafnium-tantalum coordination copolymer resin and polycarbon Silane, preferably ethylene glycol diethyl ether and xylene;

Further, the viscosity of the hafnium-tantalum-silicon ternary composite ceramic precursor solution is preferably 100-250 mPa.s, and the solid content of the solution is 50%-70%; within this range, the hafnium-tantalum-silicon ternary composite ceramics The precursor is easily impregnated into the carbon fiber preform, reducing the impregnation time;

Further, the cross-linking curing temperature is 150-350°C, and the curing time is 8-15 hours, the purpose is that the hafnium-tantalum-silicon ternary composite ceramic precursor can be fully cured in a relatively short period of time;

Step 3, placing the cross-linked and solidified preform obtained in step 2 in a cracking furnace for cracking;

The cracking is carried out in an inert atmosphere such as nitrogen or argon, and the cracking temperature is 1600-1800° C. At this temperature, a high-purity hafnium-tantalum solid solution can be obtained by cracking; the cracking time is preferably 3-5 hours ;

The high-temperature pyrolysis process of the present invention is as follows: below 1000° C., oxides of silicon carbide, hafnium and tantalum will be formed, and above 1,600° C., the oxides of hafnium and tantalum react with carbon to form a hafnium-tantalum solid solution, and silicon carbide in the matrix It forms a continuous structure with the hafnium-tantalum solid solution. In the high-temperature oxidation environment, silicon carbide will form a silicon dioxide film to prevent the diffusion of oxygen into the matrix. As a substance with an ultra-high temperature melting point, the hafnium-tantalum solid solution plays a role in maintaining the strength of the matrix , Under such cracking conditions, uniformly distributed silicon carbide and hafnium-tantalum solid solutions can be obtained, giving full play to the synergistic antioxidant effect of the two;

Step 4, using chemical vapor infiltration method to seal the pores of the composite material obtained in step 3, and deposit a silicon carbide coating with a thickness of 0.1-0.3 mm on the surface layer of the composite material.

The present invention adopts the vapor phase infiltration process to prepare the silicon carbide coating: the dense carbon/hafnium tantalum solid solution-silicon carbide substrate is placed in a vapor deposition furnace, and the chemical vapor infiltration process is used to deposit the silicon carbide coating on the surface of the substrate, and the deposition time is preferably 30 ~50 hours, the purpose is to further reduce the porosity of the matrix surface and improve the oxidation resistance of the composite material.

Further, in the described preparation method, before step 4, also comprises:

Steps 2 and 3 are repeated until the density of the composite material obtained by cracking exceeds 2.05 g/cm ³ , which aims to improve the densification degree of the carbon/hafnium tantalum solid solution-silicon carbide composite material and reduce the porosity of the composite material.

The design principle of the present invention is:

Based on the prior art, there is no carbon/hafnium-tantalum solid solution-silicon carbide ultra-high temperature ceramic matrix composite material yet. The reason is that it is difficult to make the hafnium-tantalum solid solution and silicon carbide evenly distributed by using the raw materials and methods of the prior art, such as If the existing physical blending method is used, the silicon carbide is uniformly dispersed with one of them, but not uniformly dispersed with the other, resulting in uneven dispersion of silicon carbide in the matrix of the composite material, and it is impossible to prepare a carbon/hafnium tantalum solid solution-silicon carbide with excellent performance. composite material.

The melting point of hafnium-tantalum solid solution exceeds 4000 ℃, and its anti-oxidation performance is excellent. If it is introduced into the carbon/silicon carbide matrix, it is possible to obtain ultra-high temperature ceramic matrix composites with better performance. Based on this idea, the present invention firstly prepares a uniform hafnium-tantalum-silicon ternary composite ceramic precursor solution with a controllable ratio of hafnium-tantalum-silicon. It can be adjusted and controlled, and is different from the existing physical blending. On this basis, the present invention selects a suitable preparation method, and can prepare the hafnium-tantalum solid solution and A carbon/hafnium-tantalum solid solution-silicon carbide composite material with uniform dispersion of silicon carbide and controllable ratio.

The beneficial effects of the present invention relative to the prior art:

The present invention first selects a hafnium-tantalum coordination copolymer that can provide both a hafnium source and a tantalum source. In the copolymer, hafnium and tantalum are on the same molecular chain, so that the ratio of hafnium and tantalum in the precursor can be regulated; and here On the basis, the present invention selects a suitable preparation method, and at a temperature far below the melting point of the hafnium-tantalum solid solution (1600-1800° C.), the hafnium-tantalum solid solution, the silicon carbide is uniformly dispersed and the ratio of carbon/hafnium-tantalum is controllable can be prepared. In the solid solution-silicon carbide composite material, the hafnium carbide and tantalum carbide in the composite material provided by the present invention have strong chemical bonds, can form a solid solution with a high melting point, and give full play to the synergistic antioxidant effect of hafnium carbide and tantalum carbide.

In the composite material provided by the invention, each component of the matrix is evenly distributed, and the hafnium-tantalum solid solution and silicon carbide can play a synergistic anti-oxidation effect, so that the matrix of the composite material is dense, the high-temperature mechanical properties are outstanding, and the ablation resistance, oxidation resistance, good toughness, etc. Advantages, especially excellent ablation resistance, passed the 3000 ℃ oxidative ablation assessment test. In addition, the preparation method of the present invention has the advantages of simple process, no need for any additives, low preparation temperature, short period and easy industrial implementation. And the composite material component with complex shape and near size can be prepared, which can be widely used in the preparation of components such as engine combustion chamber and tail nozzle of hypersonic aircraft, and has broad application prospects.

Detailed ways

Specific embodiments of the present invention will be described in detail below. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to assist in a comprehensive understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.

It should be noted here that the content of the present invention is not limited to the following embodiments.

Example 1

A preparation method of carbon/hafnium tantalum solid solution-silicon carbide ultra-high temperature ceramic matrix composite material, the specific steps are:

1) The needle-punched carbon fiber reinforcement is treated at a high temperature of 1700° C. for 2 hours, and then deposited in a vapor deposition furnace for 150 hours, 120 hours, and 100 hours, respectively, so that the density of the fiber reinforcement reaches 1.10 g/cm ³ ;

2) mechanically stirring 5 kilograms of hafnium-tantalum copolymer resin, 1 kilogram of polycarbosilane and 6 kilograms of allyl phenolic aldehyde for 5 hours, after standing for 10 hours, be mixed with a hafnium-tantalum-silicon ternary composite ceramic precursor solution;

3) The fiber reinforcement obtained in 1) was immersed in the precursor solution of 2), and the immersion conditions were as follows: immersion under a vacuum degree of 100KPa for 2 hours, and then immersion under a pressure of 3MPa for 2 hours. Finally, further pressurize to 10MPa, heat up to 150°C for 2 hours, keep at 200°C for 2 hours, and keep at 350°C for 4 hours, so that the hafnium-tantalum-silicon ternary composite ceramic precursor is fully cross-linked and cured;

4) Put the solidified carbon fiber reinforcement in a cracking furnace, under an argon atmosphere, crack at 1600 ° C for 4 hours;

5) Repeat steps 2) and 3) 10 times, the density of the composite material exceeds 2.2g/cm3, and the weight increase rate is less than 1%;

6) Sealing the composite material obtained in step (4) by chemical vapor infiltration method, and depositing a silicon carbide coating with a thickness of 0.1-0.3 mm on the surface layer of the composite material.

The density test of the carbon/hafnium tantalum solid solution-silicon carbide composite material prepared above was carried out by the drainage method, and the measured density was 2.36g/cm ³ , and the density of the composite material was relatively high;

The high-temperature mechanical properties of the carbon/hafnium-tantalum solid solution-silicon carbide composites prepared above were tested, and the bending strength at 1600°C reached 322MPa;

The carbon/hafnium tantalum solid solution-silicon carbide composite material prepared above was tested for ablation resistance with an oxyacetylene flame, and the ablation rate was 4.28×10-3mm/s at a high temperature of 3000°C for 20s;

The test results are shown in Table 1.

Example 2

A preparation method of carbon/hafnium tantalum solid solution-silicon carbide ultra-high temperature ceramic matrix composite material, the specific steps are:

1) The stitched carbon fiber reinforcement was treated at a high temperature of 1700° C. for 2 hours, and then deposited in a vapor deposition furnace for 150 hours, 100 hours, and 100 hours, respectively, so that the density of the fiber reinforcement reached 1.20 g/cm ³ ;

2) mechanically stirring 5 kilograms of hafnium-tantalum copolymer resin, 1 kilogram of polycarbosilane and 6 kilograms of allyl phenolic aldehyde for 5 hours, after standing for 10 hours, be mixed with a hafnium-tantalum-silicon ternary composite ceramic precursor solution;

3) The fiber reinforcement obtained in 1) was immersed in the precursor solution of 2), and the immersion conditions were as follows: immersion under a vacuum degree of 100KPa for 2 hours, and then immersion under a pressure of 3MPa for 2 hours. Finally, further pressurize to 10MPa, heat up to 150°C for 2 hours, keep at 200°C for 2 hours, and keep at 350°C for 4 hours, so that the hafnium-tantalum-silicon ternary composite ceramic precursor is fully cross-linked and cured;

4) Put the solidified carbon fiber reinforcement in a cracking furnace, under an argon atmosphere, crack at 1600 ° C for 4 hours;

5) Repeat steps 2) and 3) 9 times, the density of the composite material exceeds 2.2 g/cm ³ , and the weight increase rate is less than 1%;

6) sealing pores on the composite material obtained in step (4) by chemical vapor infiltration, and depositing a 0.1-0.3 mm thick silicon carbide coating on the surface of the composite material;

The density test of the carbon/hafnium tantalum solid solution-silicon carbide composite material prepared above was carried out by the drainage method, and the measured density was 2.39 g/cm ³ , and the density of the composite material was relatively high;

The high-temperature mechanical properties of the carbon/hafnium-tantalum solid solution-silicon carbide composites prepared above were tested, and the bending strength at 1600 °C reached 345MPa;

The carbon/hafnium-tantalum solid solution-silicon carbide composite material prepared above was tested for ablation resistance with an oxyacetylene flame, and the ablation rate was 3.34×10-3mm/s at a high temperature of 3000°C for 20s;

The test results are shown in Table 1.

Example 3

A preparation method of carbon/hafnium tantalum solid solution-silicon carbide ultra-high temperature ceramic matrix composite material, the specific steps are:

1) The finely braided punctured carbon fiber reinforcement is treated at a high temperature of 1700 ° C for 2 hours, and then deposited in a vapor deposition furnace for 150 hours, 100 hours and 100 hours respectively, so that the density of the fiber reinforcement reaches 1.23g/cm ³ ;

2) mechanically stirring 5 kilograms of hafnium-tantalum copolymer resin, 1 kilogram of polycarbosilane and 6 kilograms of allyl phenolic aldehyde for 5 hours, after standing for 10 hours, be mixed with a hafnium-tantalum-silicon ternary composite ceramic precursor solution;

3) The fiber reinforcement obtained in 1) was immersed in the precursor solution of 2), and the immersion conditions were as follows: immersion under a vacuum degree of 100KPa for 2 hours, and then immersion under a pressure of 3MPa for 2 hours. Finally, the pressure was further increased to 10MPa, and the temperature was raised to 150°C for 2 hours, 200°C for 2 hours, and 350°C for 4 hours, so that the hafnium-tantalum-silicon ternary composite ceramic precursor was fully cross-linked and cured;

4) Put the solidified carbon fiber reinforcement in a cracking furnace, under an argon atmosphere, crack at 1600 ° C for 4 hours;

5) Repeat steps 2) and 3) 9 times, the density of the composite material exceeds 2.2 g/cm ³ , and the weight increase rate is less than 1%;

6) sealing pores on the composite material obtained in step (4) by chemical vapor infiltration, and depositing a 0.1-0.3 mm thick silicon carbide coating on the surface of the composite material;

The density test of the carbon/hafnium tantalum solid solution-silicon carbide composite material prepared above was carried out by the drainage method, and the measured density was 2.41 g/cm ³ , and the density of the composite material was relatively high;

The high-temperature mechanical properties of the carbon/hafnium-tantalum solid solution-silicon carbide composites prepared above were tested, and the bending strength at 1600°C reached 367MPa;

The carbon/hafnium-tantalum solid solution-silicon carbide composite material prepared above was tested for ablation resistance with an oxyacetylene flame, and the ablation rate was 2.60×10-3mm/s at a high temperature of 3000°C for 20s;

The test results are shown in Table 1.

In addition, the results of traditional carbon/silicon carbide ceramic matrix composites and carbon/zirconium carbide-silicon carbide ceramic matrix composites under the above test conditions are shown in Table 1.

Table 1 Performance comparison of ceramic matrix composites

Table 1 shows the performance comparison of the carbon/hafnium tantalum solid solution-silicon carbide ceramic matrix composites prepared in Examples 1 to 3 with traditional carbon/silicon carbide and carbon/zirconium carbide-silicon carbide ceramic matrix composites. It can be seen that the flexural strength of the three materials at 1600 °C is basically the same. However, the line ablation rate of traditional carbon/silicon carbide ceramic matrix composites is more than 35 times that of carbon/hafnium tantalum solid solution-silicon carbide ceramic matrix composites, and the line ablation rate of carbon/zirconium carbide-silicon carbide ceramic matrix composites The rate is more than 4.5 times that of carbon/hafnium tantalum solid solution-silicon carbide ceramic matrix composites, indicating that carbon/hafnium tantalum solid solution-silicon carbide ceramic matrix composites are more efficient than traditional carbon/silicon carbide and carbon/zirconium carbide-silicon carbide ceramic matrix composites. The high temperature oxidation resistance and ablation resistance of the material has been greatly improved.

The above is a detailed description of the present invention in conjunction with the embodiments, but the embodiments of the present invention are not limited by the above-mentioned embodiments, and any other changes, substitutions, combination simplifications, etc. made under the core guiding ideology of the patent of the present invention are included in the present invention. within the scope of patent protection.

The parts of the present invention that are not described in detail are techniques known to those skilled in the art.

Claims (10)

1. a kind of ceramic matric composite, it is characterised in that: the composite material, and will be described using carbon fiber precast body as skeleton Carbon fiber precast body is impregnated in hafnium tantalum silicon ternary complex phase ceramic precursor solution and is made by solidification, cracking.

2. a kind of ceramic matric composite according to claim 1, which is characterized in that the hafnium tantalum silicon ternary complex phase pottery Porcelain precursor solution includes hafnium tantalum Coordination copolymerization resin, Polycarbosilane and carbon source presoma.

3. a kind of ceramic matric composite according to claim 2, which is characterized in that the hafnium tantalum silicon ternary complex phase pottery In porcelain precursor solution, the content of carbon source presoma is higher than hafnium tantalum Coordination copolymerization resin content.

4. a kind of ceramic matric composite according to claim 2-3, which is characterized in that the hafnium tantalum Coordination copolymerization object Resin is added the aggregated reaction of a certain amount of ligand and obtains using hafnium tetrachloride, tantalic chloride as raw material.

5. a kind of ceramic matric composite described in -4 according to claim 1, which is characterized in that the cracking temperature is 1600 ~1800 DEG C.

6. a kind of preparation method of ceramic matric composite, which comprises the following steps:

Step 1, composite preform preparation,

Carbon fibre fabric is densified, obtaining density is 1.10~1.25g/cm³Composite preform；

The crosslinking curing of step 2, composite preform,

By composite preform described in step 1 using vacuum pressure impregnation in hafnium tantalum silicon ternary complex phase ceramic precursor solution In, and carry out pressurization crosslinking curing；

Precast body after crosslinking curing that step 2 obtains is placed in pyrolysis furnace and cracks by step 3；

Step 4 carries out sealing pores to the composite material that step 3 obtains using chemical vapor infiltration, in composite layer Deposit the coat of silicon carbide of 0.1~0.3mm thickness.

7. a kind of preparation method of ceramic matric composite according to claim 6, which is characterized in that in the step 2, Hafnium tantalum silicon ternary complex phase ceramic precursor solution includes hafnium tantalum Coordination copolymerization resin, Polycarbosilane and carbon source presoma, and carbon The content of source presoma is higher than hafnium tantalum Coordination copolymerization resin content.

8. a kind of preparation method of ceramic matric composite according to claim 7, which is characterized in that the hafnium tantalum is matched Position copolymer resin is added the aggregated reaction of a certain amount of ligand and obtains using hafnium tetrachloride, tantalic chloride as raw material.

9. a kind of preparation method of ceramic matric composite according to claim 6-8, which is characterized in that the hafnium tantalum The viscosity of silicon ternary complex phase ceramic precursor solution is preferably 100~250mPa.s, and solution solid content is 50%~70%；It is described Cracking temperature be 1600~1800 DEG C.

10. a kind of preparation method of ceramic matric composite according to claim 6-9, which is characterized in that the system In Preparation Method, before step 4 further include: step 2,3 are repeated, until the density for the composite material that cracking obtains is more than 2.05g/ cm³。