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

Abstract

The invention relates to an ultra-high temperature ceramic matrix composite material with high thermal conductivity, strong bonding and ablation resistance and a preparation method thereof. The thermal conductivity of the carbon fiber is more than 40W/m·K; (2) the interface layer is deposited on the surface of the carbon fiber in the carbon fiber preform by chemical vapor infiltration; (3) by the sol-gel method, the slurry impregnation method, and the precursor impregnation method The carbon source and the ceramic phase are introduced into the carbon fiber preform by the pyrolysis method, and then combined with the reactive infiltration method to achieve densification, and the ultra-high temperature ceramic matrix composite material with high thermal conductivity, strong bonding and ablation resistance is obtained.

Description

An ultra-high temperature ceramic matrix composite material with high thermal conductivity, strong bonding and ablation resistance and its manufacture backup method

technical field

The invention relates to a method for improving the ablation resistance of a fiber-reinforced ceramic matrix composite material, in particular to a method for preparing an ultra-high temperature ceramic matrix composite material with high thermal conductivity, strong bonding and ablation resistance, belonging to the ultra-high temperature ceramic matrix composite material Preparation technology field.

Background technique

As one of the key technologies in the development of hypersonic aircraft, thermal structure is the cornerstone to ensure the safe service of aircraft in extreme environments. Its working environment is complex and severe, so it poses severe challenges to high-temperature structural materials. In order to adapt to the extreme service environment, it is necessary to overcome the problems of high strength and toughness, ultra-high temperature resistance and near-zero ablation of thermal structural materials. Continuous fiber reinforced ultra-high temperature ceramic matrix composites (Ceramic Matrix Composites) fundamentally overcome the inherent brittleness of ceramic materials, and at the same time have the advantages of light weight, ultra-high temperature resistance, oxidation ablation resistance, and strong designability, becoming a hypersonic aircraft. Important candidate material for thermal protection, thermal structure.

High temperature oxidation and ablation resistance is the most critical performance parameter of ultra-high temperature ceramic matrix composites used in extreme service environments.

SUMMARY OF THE INVENTION

Therefore, the purpose of the present invention is to provide an ultra-high temperature ceramic matrix composite material with high thermal conductivity, strong bonding and ablation resistance and a preparation method thereof, mainly by improving the thermal conductivity and matrix bonding strength of the ultra-high temperature ceramic matrix composite material. Improve the ablation resistance of the material.

On the one hand, the present invention provides a preparation method of an ultra-high temperature ceramic matrix composite material with high thermal conductivity, strong bonding and ablation resistance, comprising:

(1) Select carbon fibers to be woven into carbon fiber preforms, and the thermal conductivity of the carbon fibers is greater than 40W/m·K;

(2) using chemical vapor infiltration method to deposit an interface layer on the surface of carbon fiber in the carbon fiber preform;

(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 combined with a reactive infiltration method to achieve densification to obtain the high thermal conductivity, strong bonding, Ablation-resistant ultra-high temperature ceramic matrix composites.

The inventors found that the thermal conductivity of the material and the bonding strength of the matrix are the key factors affecting the anti-oxidative ablation performance of the ultra-high temperature ceramic matrix composite material. Moreover, during the ablation process, further studies have shown that when the thermal conductivity of the high thermal conductivity composite material is greater than 15W/m·K, it can basically transfer the heat in the ablation zone to all parts of the material quickly, avoiding heat accumulation and reducing heat. The surface temperature of the ablation zone reduces the ablation damage. At the same time, considering that the thermal conductivity of the material is closely related to the composition and structure of the material. For this reason, the present disclosure for the first time constructs carbon fiber preforms with high thermal conductivity by selecting carbon fibers with high thermal conductivity (thermal conductivity>40W/m·K), and then combines the reaction infiltration method to prepare high-density and ultra-high temperature ceramic matrix composites. In the subsequent ablation process, the composite material can quickly transfer heat to all parts of the material, avoid heat accumulation, and reduce the temperature of the ablation surface; at the same time, it can also improve the bonding strength of the composite material matrix and reduce the layered exfoliation of the material during the ablation process. It provides a new solution for improving the ablation resistance of fiber-reinforced ultra-high temperature ceramic matrix composites. Moreover, the present invention does not use a carbothermic reduction process, which ensures that the carbon fiber still has high thermal conductivity while avoiding damage to the carbon fiber caused by multiple high-temperature heat treatments.

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 carbon fiber content in the carbon fiber preform is 10-70 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 at least one of SiC, TaC, ZrC, ZrB ₂ , HfC, and HfB ₂ .

Preferably, the raw material used in the reactive infiltration method is at least one of Si, Zr, Hf, ZrSi ₂ and HfSi ₂ .

Preferably, after the carbon source and the ceramic phase are introduced, the pyrolysis is carried out in a protective atmosphere at 600-1000°C; preferably, the protective atmosphere is an inert atmosphere.

On the other hand, the present invention also provides an ultra-high temperature ceramic matrix composite material with high thermal conductivity, strong bonding and ablation resistance prepared according to the above preparation method, wherein each phase in the ultra-high temperature ceramic matrix composite material is dispersed or continuous. distribution form.

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

Preferably, the linear ablation rate of the ultra-high temperature ceramic matrix composite material is lower than 10 μm/s after being ablated under a plasma flame with a heat flux density of 4.02 MW/m ² for 60 seconds.

Beneficial effects:

The invention improves the density, bonding strength and thermal conductivity of the matrix by using carbon fibers with high thermal conductivity as reinforcements, constructing carbon fiber preforms with high thermal conductivity, and combining reactive infiltration in situ reaction methods, thereby improving the burning resistance of ultra-high temperature ceramic matrix composites. corrosion performance. During the ablation process of the ultra-high temperature ceramic matrix composite material prepared by the invention, the heat in the ablation zone can be rapidly transferred to each part of the material, the heat accumulation is reduced, and the temperature of the ablation surface is lowered. At the same time, the higher bonding strength of the substrate reduces the risk of layered erosion of the material during the ablation process, and effectively improves the ablation resistance of the material.

Description of drawings

Fig. 1 is the preparation route diagram of the ultra-high temperature ceramic matrix composite material in the present invention;

Figure 2 shows the thermal conductivity-temperature curve of the high thermal conductivity, strong bonding ultra-high temperature ceramic matrix composite material prepared in Example 1, the composite material prepared by carbothermic reduction and the traditional composite material. The thermal conductivity of the three materials decreases slightly with the increase of temperature, but the thermal conductivity of the high thermal conductivity and strong bonding ultra-high temperature ceramic matrix composites is always much higher than that of the other two composites;

Figure 3 shows the high thermal conductivity, strong bonding ultra-high temperature ceramic matrix composite material (a) prepared in Example 1, the composite material prepared by carbothermic reduction (b) and the traditional ultra-high temperature ceramic matrix composite material (c) at a heat flux density of 4.02 Optical photo after ablation for 60 seconds under MW/m ² plasma flame, it can be seen from the figure that the ablation center of the high thermal conductivity and strong bonding ultra-high temperature ceramic matrix composite has no obvious damage, but the ablation center of the other two composite materials has Obvious ablation pits.

Detailed ways

The present invention is further described below through the following embodiments, and it should be understood that the following embodiments are only used to illustrate the present invention, but not to limit the present invention.

In the present invention, based on the perspective of improving the thermal conductivity and the bonding strength of the ultra-high temperature ceramic matrix composite material, the ablation resistance of the material is improved, and specifically, a high thermal conductivity, strong bonding, and ablation resistance is provided. Preparation method of ultra-high temperature ceramic matrix composite material.

The following exemplarily illustrates the preparation method of the ultra-high temperature ceramic matrix composite material, as shown in FIG. 1 .

Fiber selection. High thermal conductivity carbon fibers are used as reinforcing fibers. Specifically, high thermal conductivity carbon fibers (thermal conductivity greater than 40 W/m·K) are used as reinforcements, which can improve the overall thermal conductivity of the composite material.

Woven fiber preform. Weaving carbon fibers into carbon fiber preforms. The fiber preform can be a 2-dimensional, 2.5-dimensional or 3-dimensional braid, preferably a 3-dimensional braid as the carbon fiber preform. In an optional embodiment, carbon fibers with a volume content of carbon fibers in the carbon fiber preform of 10 to 70 vol%, preferably 20 to 50 vol% of carbon fibers, can better absorb or impregnate the carbon source and part of the ceramic phase (or its ceramics). Precursor).

Preparation of the interface layer. The PyC layer, BN layer, SiC interface layer, (PyC/SiC) _n , or (BN/SiC) _n multilayer composite interface (n≥1) were deposited in the carbon fiber preform by chemical vapor infiltration. The thickness of the interface layer can be 0.01-5 μm, which can further prevent the carbon fibers from being damaged in the subsequent preparation process, thereby avoiding the reduction of thermal conductivity.

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

In an optional 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 make the organic carbon source or ceramic phase precursor (mainly SiC precursor such as polycarbosilane, etc.) cracked Inorganic carbon and ceramic phases are formed, respectively. Moreover, in the present invention, in order to avoid damage to the high thermal conductivity carbon fiber, the ultra-high temperature ceramic precursor and the high temperature carbothermic reduction process are not used, and the preparation process is also optimized.

Finally, the material densification process is completed by combining the reactive infiltration in-situ reaction method. The reactive infiltration raw materials can be Si, Zr, Hf, ZrSi ₂ , and HfSi ₂ . The atmosphere of the reactive infiltration may be an inert atmosphere or the like. For different reaction infiltration raw materials, the reaction temperature and time can be adjusted appropriately. For example, when the reactive infiltration raw material may be Si, the reactive infiltration temperature may be 1450-1600°C. The reaction infiltration temperature corresponding to Zr can be 1850-2000°C. The reaction infiltration temperature corresponding to Hf may be 2250-2500°C. The reaction infiltration temperature corresponding to ZrSi ₂ can be 1620-2000°C. The corresponding reaction infiltration temperature of HfSi ₂ can be 1680-2000°C. Moreover, the reactive infiltration process reduces the porosity of the composite material and increases the density of the composite material matrix, which can reduce the phonon scattering during the heat transfer process and improve the thermal conductivity of the material. At the same time, the reactive infiltration process also improves the bonding strength of the composite matrix, which can further reduce the risk of laminar peeling of the material during the ablation process (risk of being ablated by high-speed airflow), and improve the ablation resistance of the material.

In the present invention, the thermal conductivity of the ultra-high temperature ceramic matrix composite material measured at 1200° C. is greater than 15W·m ⁻¹ ·K ⁻¹ by using a flash thermal conductivity meter (NETZSCH LFA467 HT, Germany).

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

In the present invention, the interlaminar bonding strength of the ultra-high temperature ceramic matrix composite material measured by the interlaminar shear test method is greater than 40 MPa.

In the present invention, during the ablation process of the prepared ultra-high temperature ceramic matrix composite material, the heat in the ablation zone can be rapidly transferred to each part of the material, thereby reducing heat accumulation and lowering the surface temperature of the material. The linear ablation rate of ultra-high temperature ceramic matrix composites measured by plasma flame (PlasmerJet, A-2000, Sulzer Metco, Switzerland) under plasma flame with heat flux density of ^4.02MW /m2 (~2200℃) is less than 10μm/s , preferably below 1 μm/s.

The following further examples are given to illustrate 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 content of the present invention belong to the present invention. scope of protection. The specific process parameters and the like in the following examples are only an example of a suitable range, that is, those skilled in the art can make selections within the suitable range through the description herein, and are not intended to be limited to the specific numerical values exemplified below.

Example 1

A preparation method of a high thermal conductivity, strong bonding, ablation resistant ultra-high temperature ceramic matrix composite material, the specific steps are:

(1) Fiber selection: select high thermal conductivity carbon fiber with thermal conductivity of 60W/m K as the composite material reinforcement;

(2) Braided carbon fiber preform: a carbon fiber preform is prepared by 2-dimensional stitching, and the volume content of carbon fiber in the preform is ~30 vol%;

(3) Preparation of interface layer: A PyC/SiC composite interface layer was deposited on the surface of the above-mentioned preform fiber by chemical vapor infiltration method. The total thickness of the deposited PyC/SiC composite interface layer is ~0.5 μm;

(4) Introduction of ceramic matrix: use phenolic resin and polyvinylpyrrolidone as carbon source, ethanol as solvent, and mix with ZrC powder with particle size of 1-3 μm to form slurry. ZrC powder accounts for 60wt% of the slurry, and carbon source accounts for 10wt%. The carbon fiber preform in (3) is impregnated under the condition that the vacuum degree is -0.07MPa～-0.10MPa, and the impregnation time is 2 hours. The obtained carbon fiber preform was dried at 80 °C for 6 h, and then cracked at 800 °C under an Ar protective atmosphere. Finally, Si was infiltrated under the conditions of 1500 ℃ and 1-10 Pa to complete the densification of the material, and the C _f /ZrC-SiC composite material was obtained.

The open porosity of the obtained C _f /ZrC-SiC composite material is ~5vol%, the interlayer bonding strength is 50MPa, and the thermal conductivity of the material below 1200°C is greater than 15W·m ^-1 ·K ^-1 (as shown in Figure 2). The material was plasma ablated for 60s at a heat flux density of 4.02MW/m ² (the temperature of the ablation center was ~2250℃), and the ablation center had no obvious damage (as shown in Figure 3), and the linear ablation rate was only 0.06μm/s.

Example 2

Similar to the steps in Example 1, the difference is that: in step (2), the carbon fibers are arranged in a 3-dimensional acupuncture form, and the ratio of XYZ-oriented fibers is 10:10:1. The carbon fiber content in the carbon fiber preform was -40 vol%.

The open porosity of the obtained C _f /ZrC-SiC composite material is ~4vol%, the interlayer bonding strength is 50MPa, and the thermal conductivity of the material below 1200℃ is greater than 20W·m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2100℃), the linear ablation rate was 0.03μm/s.

Example 3

Similar to the steps in Example 1, the difference is that: in step (3), chemical vapor infiltration is used to deposit a (PyC/SiC) ₃ multi-layer composite interface layer on the fiber surface, with a total thickness of ~3 μm.

The porosity of the obtained C _f /ZrC-SiC composite material is ~6vol%, the interlayer bonding strength is 55MPa, and the thermal conductivity of the material below 1200°C is greater than 18W·m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2200℃), the linear ablation rate was 0.06μm/s.

Example 4

Similar to the steps in Example 1, the difference is that in step (4), sucrose is used as the carbon source of the slurry, and the carbon source accounts for 15-30 wt% of the slurry.

The obtained C _f /ZrC-SiC composite material (carbon source accounts for 15wt% of the slurry) has a porosity of ~4vol%, an interlayer bonding strength of 50MPa, and a thermal conductivity below 1200°C greater than 20W·m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2100℃), the linear ablation rate was 0.06μm/s.

Example 5

Similar to the steps in Example 1, the difference is: in step (4), the precursor slurry adopts a mixture of 1-3 μm ZrB ₂ powder and polycarbosilane, and the ZrB ₂ powder accounts for 40-40% of the mixed precursor slurry. 80wt%.

The obtained C _f /ZrB ₂ -SiC composite material (ZrB ₂ powder accounts for 60wt% of the mixed precursor slurry) has a porosity of ~4vol%, the interlayer bonding strength is 60MPa, and the thermal conductivity of the material below 1200°C is greater than 15W·m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2200℃), the linear ablation rate was 0.03μm/s.

Example 6

Similar to the steps in Example 1, the difference is: in step (4), the mixed powder of ZrB ₂ of 1-3 μm and ZrC of 1-3 μm is used as the ceramic filler in the precursor slurry, and the mixed powder accounts for the mixed precursor slurry. The mass ratio of ZrB ₂ and ZrC is 1:1.

The obtained C _f /ZrB ₂ -ZrC-SiC composite material (mixed powder accounts for 70wt% of the mixed precursor slurry) has a porosity of ~4vol%, the interlayer bonding strength is 55MPa, and the thermal conductivity of the material below 1200°C is greater than 17W· m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2200℃), the linear ablation rate was 0.03μm/s.

Example 7

Similar to the steps in Example 1, the difference is that: in step (4), ZrSi ₂ is used to perform reactive infiltration and densification of the material under the conditions of 1700° C. and 1-10 Pa.

The porosity of the obtained C _f /ZrC-SiC composite material is ~5vol%, the interlayer bonding strength is 53MPa, and the thermal conductivity of the material below 1200°C is greater than 20W·m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2100℃), the linear ablation rate was 0.03μm/s.

Example 8

Similar to the step in Example 1, the difference is: in step (4), Zr is used to carry out reactive infiltration and densification of the material at 1900° C. and 1-10 Pa.

The porosity of the obtained composite material is ~5vol%, the interlayer bonding strength is 50MPa, and the thermal conductivity of the material below 1200°C is greater than 17W·m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2100℃), the linear ablation rate was 0.04μm/s.

Example 10

Similar to the steps in Example 1, the difference is that: in step (4), HfSi ₂ is used to carry out reactive infiltration and densification of the material under the conditions of 1700° C. and 1-10 Pa.

The porosity of the obtained composite material is ~4vol%, the interlayer bonding strength is 53MPa, and the thermal conductivity of the material below 1200°C is greater than 18W·m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2150℃), the linear ablation rate was 0.03μm/s.

Comparative Example 1

Similar to the steps in Example 1, the difference is: in step (4), the organic Zr precursor (PZC) and carbon are used as the slurry to impregnate the fibers under vacuum at 1 to 10 Pa, and then cracked at 800 ° C under Ar protective atmosphere. , followed by carbothermic reduction at 1700 °C for 2 hours, and then infiltration and densification using Si reaction.

The porosity of the obtained C _f /ZrC-SiC composite material is ~5vol%, the interlayer bonding strength is 35MPa, and the thermal conductivity of the material below 1200°C is less than 10W·m ^-1 ·K ^-1 . After the material was ablated by 4.02MW/m ² plasma for 60s (ablation center temperature～2600℃), the linear ablation rate was 30μm/s.

Comparative Example 2

Preparation of traditional ultra-high temperature ceramic matrix composites:

Step 1: Select conventional three-dimensional acupuncture carbon fiber as fiber reinforcement;

Step 2: using chemical vapor infiltration method to deposit a PyC/SiC composite interface layer on the surface of the above-mentioned prefabricated fibers, with a thickness of ~0.5 μm;

Step 3: use organic Zr precursor (PZC) and polycarbosilane precursor to vacuum impregnate the material obtained in step 2 under a vacuum of 0-10Pa, and keep it for 1h;

Step 4: Incubate at 800-1200°C under an argon atmosphere for 2h, and crack the material obtained in step 3;

Step 5: Carbothermal reduction under argon atmosphere at 1500-1800°C for 2h;

Step 6: Repeat steps 3 to 5 until a dense C _f /ZrC-SiC composite material is obtained.

The porosity of the obtained C _f /ZrC-SiC composite material is ~15vol%, the interlayer bonding strength is 32MPa, and the thermal conductivity of the material below 1200°C is less than 5W·m ^-1 ·K ^-1 . After the material was ablated by plasma at 4.02MW/m ² for 60s (ablation center temperature～2800℃), the linear ablation rate was 41μm/s.

Claims (10)

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:

(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.

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.

Images