CN111454073A

CN111454073A - High-heat-conductivity, strong-bonding and ablation-resistant ultrahigh-temperature ceramic matrix composite and preparation method thereof

Info

Publication number: CN111454073A
Application number: CN202010326441.6A
Authority: CN
Inventors: 倪德伟; 陈博文; 董绍明; 陈小武; 何平; 王震; 丁玉生; 张翔宇
Original assignee: Shanghai Institute of Ceramics of CAS
Current assignee: Shanghai Institute of Ceramics of CAS
Priority date: 2020-04-23
Filing date: 2020-04-23
Publication date: 2020-07-28

Abstract

The invention relates to an ultra-high temperature ceramic matrix composite material with high heat conductivity, strong bonding and ablation resistance and a preparation method thereof, wherein the preparation method of the ultra-high temperature ceramic matrix composite material comprises the following steps: (1) selecting carbon fibers to weave into a carbon fiber preform, wherein the thermal conductivity of the carbon fibers is more than 40W/m.K; (2) depositing an interface layer on the surface of the carbon fiber in the carbon fiber preform by adopting a chemical vapor infiltration method; (3) introducing a carbon source and a ceramic phase into the carbon fiber preform by a sol-gel method, a slurry impregnation method and a precursor impregnation cracking method, and then realizing densification by combining with a reaction infiltration method to obtain the ultrahigh-temperature ceramic matrix composite material with high heat conductivity, strong bonding and ablation resistance.

Description

High-heat-conductivity, strong-bonding and ablation-resistant ultrahigh-temperature ceramic matrix composite and preparation method thereof

Technical Field

The invention relates to a method for improving ablation resistance of a fiber-reinforced ceramic matrix composite, in particular to a preparation method of a high-heat-conductivity, strong-bonding and ablation-resistant ultrahigh-temperature ceramic matrix composite, and belongs to the technical field of preparation of ultrahigh-temperature ceramic matrix composites.

Background

As one of the key technologies for developing hypersonic aircrafts, a thermal structure is a foundation stone for guaranteeing the safety service of the aircrafts in extreme environments, and the working environment is complex and severe, so that a severe challenge is provided for high-temperature structural materials. In order to adapt to extreme service environment, the problems of high toughness, ultrahigh temperature resistance and near-zero ablation of thermal structural materials must be overcome. The continuous fiber reinforced ultra-high temperature Ceramic Matrix composite (Ceramic Matrix Composites) fundamentally overcomes the inherent brittleness of Ceramic materials, has the advantages of light weight, ultra-high temperature resistance, oxidation ablation resistance, strong designability and the like, and becomes an important candidate material for the thermal protection and the thermal structure of a hypersonic aircraft.

The high-temperature oxidation-resistant ablation is the most key performance parameter of the ultrahigh-temperature ceramic-based composite material applied to the extreme service environment.

Disclosure of Invention

Therefore, the invention aims to provide the ultrahigh-temperature ceramic-based composite material with high heat conductivity, strong bonding and ablation resistance and the preparation method thereof, and the ablation resistance of the material is improved mainly by improving the heat conductivity and the bonding strength of a matrix of the ultrahigh-temperature ceramic-based composite material.

On one hand, the invention provides a preparation method of a high-heat-conductivity, strong-bonding and ablation-resistant ultrahigh-temperature ceramic matrix composite, which comprises the following steps:

(1) selecting carbon fibers to weave into a carbon fiber preform, wherein the thermal conductivity of the carbon fibers is more than 40W/m.K;

(2) depositing an interface layer on the surface of the carbon fiber in the carbon fiber preform by adopting a chemical vapor infiltration method;

(3) introducing a carbon source and a ceramic phase into the carbon fiber preform by a sol-gel method, a slurry impregnation method and a precursor impregnation cracking method, and then realizing densification by combining with a reaction infiltration method to obtain the ultrahigh-temperature ceramic matrix composite material with high heat conductivity, strong bonding and ablation resistance.

The inventor finds that the thermal conductivity of the material and the bonding strength of the matrix are key factors influencing the anti-oxidation and ablation performance of the ultra-high temperature ceramic matrix composite. In the ablation process, further research shows that when the thermal conductivity of the high-thermal conductivity composite material is more than 15W/m.K, the composite material can basically and rapidly transfer the heat in an ablation area to each part of the material, avoid heat accumulation and reduce the surface temperature of the ablation area so as to reduce ablation damage. Meanwhile, the thermal conductivity of the material is closely related to the composition and structure of the material. Therefore, the high-density ultrahigh-temperature ceramic-based composite material is prepared by selecting the carbon fiber with high thermal conductivity (the thermal conductivity is more than 40W/m.K) to construct a carbon fiber preform with high thermal conductivity for the first time and combining a reaction infiltration method, so that the composite material can rapidly transmit heat to each part of the material in the subsequent ablation process, the heat accumulation is avoided, and the ablation surface temperature is reduced; meanwhile, the bonding strength of the matrix of the composite material can be improved, the risk of layered erosion of the material in the ablation process is reduced, and a new solution is provided for improving the ablation resistance of the fiber-reinforced ultrahigh-temperature ceramic matrix composite material. In addition, the invention does not adopt the carbothermic reduction process, avoids the damage of the carbon fiber caused by multiple high-temperature heat treatments, and ensures that the carbon fiber still has high thermal conductivity.

Preferably, the carbon fiber preform is a 2-dimensional fiber preform, a 2.5-dimensional fiber preform, or a 3-dimensional fiber preform.

Preferably, the content of the carbon fiber in the carbon fiber preform is 10 to 70 vol%.

Preferably, the interface layer is at least one of a PyC layer, a BN layer and a SiC interface layer; the total thickness of the interface layer is 0.01-5 μm.

Preferably, the carbon source is at least one of phenolic resin, polyvinylpyrrolidone, sucrose and carbon powder.

Preferably, the ceramic phase is SiC, TaC, ZrC, ZrB₂、HfC、HfB₂At least one of (1).

Preferably, the raw materials used in the reaction infiltration method are Si, Zr, Hf and ZrSi₂、HfSi₂At least one of (1).

Preferably, after introducing the carbon source and the ceramic phase, cracking the ceramic phase in a protective atmosphere at 600-1000 ℃; preferably, the protective atmosphere is an inert atmosphere.

On the other hand, the invention also provides the ultrahigh-temperature ceramic-based composite material with high thermal conductivity, strong bonding and ablation resistance, which is prepared according to the preparation method, wherein each phase in the ultrahigh-temperature ceramic-based composite material is in a dispersion distribution or continuous distribution form.

Preferably, the open porosity of the ultrahigh-temperature ceramic matrix composite is lower than 10%, the thermal conductivity is greater than 15W/m.K, and the interlayer bonding strength is greater than 40 MPa.

Preferably, the heat flux density is 4.02MW/m²After the ultra-high temperature ceramic matrix composite is ablated for 60 seconds under the plasma flame, the line ablation rate of the ultra-high temperature ceramic matrix composite is lower than 10 mu m/s.

Has the advantages that:

according to the invention, the density, the bonding strength and the thermal conductivity of the matrix are improved by using the high-thermal-conductivity carbon fiber as a reinforcement, constructing a high-thermal-conductivity carbon fiber preform and combining a reaction infiltration in-situ reaction method, so that the ablation resistance of the ultrahigh-temperature ceramic-based composite material is improved. The ultra-high temperature ceramic matrix composite prepared by the invention can rapidly transmit the heat of an ablation area to each part of the material in the ablation process, reduce the heat accumulation and reduce the ablation surface temperature. Meanwhile, the higher bonding strength of the matrix reduces the risk of layered ablation of the material in the ablation process and effectively improves the ablation resistance of the material.

Drawings

FIG. 1 is a schematic diagram of the preparation route of the ultra-high temperature ceramic matrix composite material according to the present invention;

fig. 2 is a thermal conductivity-temperature curve of the composite material prepared by carbothermic reduction and the traditional composite material of the high thermal conductivity and strong bonding ultra-high temperature ceramic-based composite material prepared in example 1, and it can be seen from the graph that the thermal conductivities of the three materials are slightly reduced along with the temperature increase from room temperature to 1200 ℃, but the thermal conductivity of the high thermal conductivity and strong bonding ultra-high temperature ceramic-based composite material is always much higher than that of the other two composite materials;

FIG. 3 shows the heat flux density of the high thermal conductivity, strong bond ultra-high temperature ceramic matrix composite (a), the composite (b) prepared by carbothermic reduction, and the conventional ultra-high temperature ceramic matrix composite (c) prepared in example 1 at 4.02MW/m²The photo after the composite material is ablated for 60 seconds under plasma flame shows that the ablation center of the ultrahigh-temperature ceramic-based composite material with high thermal conductivity and strong bonding has no obvious damage, but the ablation centers of the other two composite materials have obvious ablation pits.

Detailed Description

The present invention is further illustrated by the following examples, which are to be understood as merely illustrative and not restrictive.

In the invention, the ablation resistance of the material is improved based on the angles of improving the heat conductivity and the matrix bonding strength of the ultra-high temperature ceramic matrix composite, and particularly, the preparation method of the ultra-high temperature ceramic matrix composite with high heat conductivity, strong bonding and ablation resistance is provided.

The following is an exemplary description of the method of making an ultra high temperature ceramic matrix composite, as shown in FIG. 1.

And (4) selecting fibers. Highly thermally conductive carbon fibers are used as reinforcing fibers. Specifically, the thermal conductivity of the entire composite material can be improved by using high thermal conductivity carbon fibers (thermal conductivity greater than 40W/m.K) as the reinforcement.

And weaving the fiber preform. Weaving the carbon fibers into a carbon fiber preform. The fiber preform may be a 2-dimensional, 2.5-dimensional or 3-dimensional woven body, preferably a 3-dimensional woven body as a carbon fiber preform. In an alternative embodiment, the carbon fiber preform contains carbon fibers in an amount of 10 to 70vol%, preferably 20 to 50 vol%, and can better absorb or impregnate the carbon source and part of the ceramic phase (or the ceramic precursor thereof).

And preparing an interface layer. Depositing PyC layer, BN layer, SiC interface layer, (PyC/SiC) in carbon fiber preform by chemical vapor infiltration_nOr (BN/SiC)_nMultilayer composite interface (n is more than or equal to 1). The thickness of the interface layer can be 0.01-5 mu m, and the carbon fiber can be further prevented from being damaged in the subsequent preparation process, so that the reduction of the thermal conductivity is avoided.

A carbon source and a part of a ceramic phase are introduced into a carbon fiber preform. Specific methods include, but are not limited to, sol-gel methods, slurry impregnation methods, precursor impregnation cracking methods, and the like. The carbon source can be organic carbon source or/and inorganic carbon source, such as phenolic resin, polyvinylpyrrolidone, sucrose, and carbon powder. Wherein the ceramic phase can be SiC, TaC, ZrC, ZrB₂、HfC、HfB₂And the like. When the ceramic phase is introduced, ceramic powder corresponding to the ceramic or an organic precursor (mainly referring to a SiC precursor such as polycarbosilane) corresponding to the ceramic can be selected. As an example of vacuum impregnation, after vacuum is applied (the degree of vacuum may be 0 to 10Pa), a carbon fiber preform may be impregnated in a slurry containing a carbon source and a part of a ceramic phase, and dried after being maintained for 0.5 to 2 hours. Wherein the content of the carbon source in the slurry can be 5-30 wt%. The content of the ceramic phase (or the organic precursor corresponding to the ceramic phase) in the slurry can be 30-80 wt%. The organic solvent used in the slurry can be ethanol, acetone, gasoline, xylene, etc.

In an alternative embodiment, after the introduction of the carbon source and part of the ceramic phase, a drying and cracking process may be performed in order to crack the organic carbon source or the ceramic phase precursor (mainly referring to SiC precursors such as polycarbosilane) to form the inorganic carbon and the ceramic phase, respectively. In addition, in order to avoid damaging the high-thermal-conductivity carbon fibers, the ultrahigh-temperature ceramic precursor and the high-temperature carbothermic reduction process are not adopted, and the preparation process is optimized.

Finally combined reaction infiltration in-situ reaction methodThe method completes the densification process of the material. The reaction infiltration raw material can be Si, Zr, Hf, ZrSi₂、HfSi₂In (1). The atmosphere of the reaction infiltration may be an inert atmosphere or the like. The reaction temperature and time can be adjusted for different reaction infiltration raw materials. For example, when the reactive infiltration raw material may be Si, the reactive infiltration temperature may be 1450-1600 ℃. The reaction infiltration temperature corresponding to Zr can be 1850-2000 ℃. The reaction infiltration temperature corresponding to Hf may be 2250-2500 ℃. ZrSi₂The corresponding reaction infiltration temperature can be 1620-2000 ℃. HfSi₂The corresponding reaction infiltration temperature can be 1680-2000 ℃. In addition, the porosity of the composite material is reduced in the reaction infiltration process, the density of the matrix of the composite material is improved, phonon scattering in the heat transmission process can be reduced, and the heat conductivity of the material is improved. Meanwhile, the bonding strength of the composite material matrix is improved in the reaction infiltration process, the risk of layered peeling of the material in the ablation process (the risk of ablation by high-speed airflow) can be further reduced, and the ablation resistance of the material is improved.

In the invention, the thermal conductivity of the ultra-high temperature ceramic matrix composite material at 1200 ℃ is more than 15 W.m measured by a flash method thermal conductivity meter (Germany NETZSCH L FA467 HT)^-1·K^-1。

In the present invention, the open porosity of the ultra-high temperature ceramic matrix composite measured by Archimedes drainage method is less than 10 vol%, preferably less than 5 vol%.

In the invention, the interlayer bonding strength of the ultrahigh-temperature ceramic matrix composite material is measured to be more than 40MPa by adopting an interlayer shear test method.

In the invention, the prepared ultrahigh-temperature ceramic-based composite material can rapidly transmit the heat of an ablation area to each part of the material in the ablation process, thereby reducing the heat accumulation and lowering the surface temperature of the material. The heat flow density of the ultrahigh-temperature ceramic matrix composite material is measured to be 4.02MW/m by adopting a plasma flame (Plasmerjet, A-2000, Sulzer Metco, Switzerland)²Has a line ablation rate of less than 10 μm/s, preferably less than 1 μm/s, under a plasma flame (. about.2200 ℃).

The present invention will be described in further detail with reference to examples. It is also to be understood that the following examples are illustrative of the present invention and are not to be construed as limiting the scope of the invention, and that certain insubstantial modifications and adaptations of the invention by those skilled in the art may be made in light of the above teachings. The specific process parameters and the like of the following examples are also only one example of suitable ranges, i.e., those skilled in the art can select the appropriate ranges through the description herein, and are not limited to the specific values exemplified below.

Example 1

A preparation method of a high-heat-conductivity, strong-bonding and ablation-resistant ultrahigh-temperature ceramic matrix composite material comprises the following specific steps:

(1) selecting fibers: selecting high-thermal-conductivity carbon fibers with the thermal conductivity of 60W/m.K as a composite material reinforcement;

(2) weaving a carbon fiber preform: preparing a carbon fiber preform by adopting a 2-dimensional sewing mode, wherein the volume content of carbon fibers in the preform is-30 vol%;

(3) preparing an interface layer: and depositing a PyC/SiC composite interface layer on the surface of the preform fiber by adopting a chemical vapor infiltration method. The total thickness of the deposited PyC/SiC composite interface layer is 0.5 mu m;

(4) introducing a ceramic matrix: phenolic resin and polyvinylpyrrolidone are used as carbon sources, ethanol is used as a solvent, and the carbon sources and the ethanol are mixed with ZrC powder with the grain diameter of 1-3 mu m to form slurry. The ZrC powder accounts for 60 wt% of the slurry, and the carbon source accounts for 10 wt%. And (3) dipping the carbon fiber preform in the step (3) under the condition that the vacuum degree is-0.07 MPa to-0.10 MPa, wherein the dipping time is 2 hours. The obtained carbon fiber preform was dried at 80 ℃ for 6 hours and then cracked at 800 ℃ under Ar protective atmosphere. Finally, Si is infiltrated under the conditions of 1500 ℃ and 1-10 Pa to finish the densification of the material, and C is obtained_fthe/ZrC-SiC composite material.

Obtained as described above C_fThe opening porosity of the/ZrC-SiC composite material is 5 vol%, the interlayer bonding strength is 50MPa, and the thermal conductivity of the material below 1200 ℃ is more than 15 W.m^-1·K^-1(as shown in fig. 2). The material has a heat flow density of 4.02MW/m²Plasma ablation is carried out for 60s (the temperature of an ablation center is 2250 ℃), the ablation center has no obvious damage (as shown in figure 3), and line ablation is carried outThe ratio was only 0.06. mu.m/s.

Example 2

Similar to the procedure in example 1, except that: the arrangement mode of the carbon fibers in the step (2) is a 3-dimensional needling mode, and the ratio of XYZ-oriented fibers is 10:10: 1. The carbon fiber content in the carbon fiber preform is 40 vol%.

Obtained C_fThe opening porosity of the/ZrC-SiC composite material is 4 vol%, the interlayer bonding strength is 50MPa, and the thermal conductivity of the material below 1200 ℃ is more than 20 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (ablation center temperature-2100 ℃), the linear ablation rate is 0.03 μm/s.

Example 3

Similar to the procedure in example 1, except that: step (3) depositing (PyC/SiC) on the surface of the fiber by adopting a chemical vapor infiltration method₃The total thickness of the multilayer composite interface layer is 3 mu m.

Obtained C_fthe/ZrC-SiC composite material has the porosity of 6 vol%, the interlayer bonding strength of 55MPa, and the thermal conductivity of the material below 1200 ℃ of more than 18 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (the ablation center temperature is 2200 ℃), the linear ablation rate is 0.06 mu m/s.

Example 4

Similar to the procedure in example 1, except that: in the step (4), cane sugar is used as a slurry carbon source, and the carbon source accounts for 15-30 wt% of the slurry.

Obtained C_fthe/ZrC-SiC composite material (carbon source accounts for 15 wt% of the slurry) has the porosity of 4 vol%, the interlayer bonding strength of 50MPa and the thermal conductivity of the material below 1200 ℃ of more than 20 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (ablation center temperature-2100 ℃), the linear ablation rate is 0.06 μm/s.

Example 5

Similar to the procedure in example 1, except that: ZrB with the thickness of 1-3 mu m is adopted as the precursor slurry in the step (4)₂Mixture of powder and polycarbosilane, ZrB₂The powder accounts for 40-80 wt% of the mixed precursor slurry.

Obtained C_f/ZrB₂-SiC composite material (ZrB)₂Powder accounts for 60wt percent of the mixed precursor slurry), the porosity is 4vol percent, the interlayer bonding strength is 60MPa, and the thermal conductivity of the material below 1200 ℃ is more than 15 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (ablation center temperature-2200 ℃), the linear ablation rate is 0.03 μm/s.

Example 6

Similar to the procedure in example 1, except that: ZrB with the thickness of 1-3 mu m is adopted in the precursor slurry in the step (4)₂And 1-3 mu m ZrC mixed powder as ceramic filler, wherein the mixed powder accounts for 40-80 wt% of the mixed precursor slurry, and ZrB₂And ZrC in a mass ratio of 1: 1.

obtained C_f/ZrB₂The porosity of the-ZrC-SiC composite material (the mixed powder accounts for 70 wt% of the mixed precursor slurry) is 4 vol%, the interlayer bonding strength is 55MPa, and the thermal conductivity of the material below 1200 ℃ is more than 17 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (ablation center temperature-2200 ℃), the linear ablation rate is 0.03 μm/s.

Example 7

Similar to the procedure in example 1, except that: ZrSi is used in the step (4)₂The material is subjected to reactive infiltration densification at 1700 ℃ under the condition of 1-10 Pa.

Obtained C_fthe/ZrC-SiC composite material has the porosity of 5 vol%, the interlayer bonding strength of 53MPa, and the thermal conductivity of the material below 1200 ℃ of more than 20 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (ablation center temperature-2100 ℃), the linear ablation rate is 0.03 μm/s.

Example 8

Similar to the procedure in example 1, except that: in the step (4), Zr is used for carrying out reaction infiltration densification on the material under the conditions of 1900 ℃ and 1-10 Pa.

The porosity of the obtained composite material is 5 vol%, the interlayer bonding strength is 50MPa, and the thermal conductivity of the material below 1200 ℃ is more than 17 W.m^-1·K^-1. The material is 4.02MW/m²Plasma ablationAfter 60s (ablation center temperature-2100 ℃), the linear ablation rate is 0.04 μm/s.

Example 10

Similar to the procedure in example 1, except that: using HfSi in step (4)₂And carrying out reaction infiltration densification on the material at 1700 ℃ under the condition of 1-10 Pa.

The porosity of the obtained composite material is 4 vol%, the interlayer bonding strength is 53MPa, and the thermal conductivity of the material below 1200 ℃ is more than 18 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (ablation center temperature-2150 ℃), the linear ablation rate is 0.03 μm/s.

Comparative example 1

Similar to the procedure in example 1, except that: and (4) firstly, using an organic Zr Precursor (PZC) and carbon as slurry to vacuum-impregnate the fiber under 1-10 Pa, firstly cracking at 800 ℃ under Ar protective atmosphere, then performing carbothermic reduction at 1700 ℃ for 2 hours, and then performing infiltration densification by using Si reaction.

Obtained C_fthe/ZrC-SiC composite material has the porosity of 5 vol%, the interlayer bonding strength of 35MPa, and the thermal conductivity of the material below 1200 ℃ of less than 10 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (ablation center temperature-2600 ℃), the linear ablation rate is 30 μm/s.

Comparative example 2

Preparation of traditional ultra-high temperature ceramic matrix composite:

step 1: selecting conventional three-dimensional needled carbon fibers as a fiber reinforcement;

step 2: depositing a PyC/SiC composite interface layer on the surface of the prefabricated fiber by adopting a chemical vapor infiltration method, wherein the thickness of the PyC/SiC composite interface layer is 0.5 mu m;

and step 3: vacuum dipping the material obtained in the step 2 by using an organic Zr Precursor (PZC) and a polycarbosilane precursor under the vacuum degree of 0-10Pa, and keeping for 1 h;

and 4, step 4: preserving the heat for 2h at 800-1200 ℃ under the argon atmosphere, and cracking the material obtained in the step 3;

and 5: performing carbothermal reduction for 2h at the temperature of 1500 plus 1800 ℃ under the argon atmosphere;

step 6: repeating the steps 3 to 5 until compact C is obtained_fthe/ZrC-SiC composite material.

Obtained C_fthe/ZrC-SiC composite material has the porosity of 15 vol%, the interlayer bonding strength of 32MPa, and the thermal conductivity of the material below 1200 ℃ of less than 5 W.m^-1·K^-1. The material is 4.02MW/m²After plasma ablation for 60s (ablation center temperature-2800 ℃), the line ablation rate was 41 μm/s.

Claims

1. A preparation method of a high-heat-conductivity, strong-bonding and ablation-resistant ultrahigh-temperature ceramic matrix composite material is characterized by comprising the following steps of:

2. The production method according to claim 1, wherein the carbon fiber preform is a 2-dimensional fiber preform, a 2.5-dimensional fiber preform, or a 3-dimensional fiber preform; the content of carbon fiber in the carbon fiber preform is 10-70 vol%.

3. The production method according to claim 1 or 2, wherein the interface layer is at least one of a PyC layer, a BN layer, and a SiC interface layer; the total thickness of the interface layer is 0.01-5 μm.

4. The method according to any one of claims 1 to 3, wherein the carbon source is at least one of a phenol resin, polyvinylpyrrolidone, sucrose, and carbon powder.

5. The production method according to any one of claims 1 to 4, wherein the ceramic phase is SiC, TaC, ZrC, ZrB₂、HfC、HfB₂At least one of (1).

6. The preparation method according to any one of claims 1 to 5, characterized in that after the introduction of the carbon source and the ceramic phase, the cracking is carried out in a protective atmosphere at 600 to 1000 ℃; preferably, the protective atmosphere is an inert atmosphere.

7. The production method according to any one of claims 1 to 6, wherein the raw material for the reaction infiltration method is Si, Zr, Hf, ZrSi₂、HfSi₂At least one of (1).

8. The superhigh temperature ceramic-based composite material with high thermal conductivity, strong bonding and ablation resistance, which is prepared according to the preparation method of any one of claims 1 to 7, is characterized in that the phases in the superhigh temperature ceramic-based composite material are in a dispersion distribution or continuous distribution mode.

9. The ultrahigh-temperature ceramic-based composite material according to claim 8, wherein the ultrahigh-temperature ceramic-based composite material has an open porosity of less than 10%, a thermal conductivity of greater than 15W/m-K, and an interlayer bond strength of greater than 40 MPa.

10. The ultrahigh-temperature ceramic-based composite material according to claim 8 or 9, characterized in that the heat flux density is 4.02MW/m²After the ultra-high temperature ceramic matrix composite is ablated for 60 seconds under the plasma flame, the line ablation rate of the ultra-high temperature ceramic matrix composite is lower than 10 mu m/s.