CN114524674A - Heat-proof, heat-insulation and load-bearing integrated light carbon-ceramic composite material and preparation method thereof - Google Patents

Abstract

The invention discloses a heat-proof, heat-insulation and load-bearing integrated light carbon-ceramic composite material and a preparation method thereof, and belongs to the technical field of ultrahigh-temperature thermal protection materials. The composite material is prepared by compounding a ceramic matrix with oxidation resistance and ablation resistance with a light carbon-based composite material. The material consists of a fiber reinforcement body, carbon aerogel and a ceramic double-base body, wherein the ceramic base body is uniformly dispersed in a carbon aerogel three-dimensional nano network structure, and the multifunctional requirement under a long-term high-temperature aerobic environment is met by means of heat insulation-bearing of the carbon aerogel and anti-oxidation ablation of the ceramic base body. By changing the types, contents and introduction sequence of ceramic components, the wide-temperature-range oxidation and ablation resistance of the light carbon-based composite material can be realized. Compared with a light carbon-based composite material, the mechanical and oxidation resistance of the material provided by the invention is obviously improved, the compression strength is improved to 90.9MPa, and the weight loss rate of static oxidation for 15min at 1300 ℃ is reduced to 9.19%.

Description

Heat-proof-heat-insulation-load-bearing integrated lightweight carbon-ceramic composite material and preparation method thereof

technical field

The invention relates to the technical field of ultra-high temperature thermal protection materials, in particular to a heat-proof-heat-insulation-bearing integrated lightweight carbon-ceramic composite material and a preparation method thereof.

Background technique

Carbon aerogel is a new type of nano-scale porous carbon material. Three-dimensional nano-carbon particles are stacked in it to form a rich pore structure, making it both lightweight and porous for aerogels and carbon materials are stable at high temperature. Excellent properties. In particular, due to its unique mesoporous structure and nanoparticle network structure for phonon scattering, photon shielding, and suppression of gas molecule collisions, it can greatly reduce solid-state, gaseous and radiative thermal conductivity, and its thermal insulation performance is significantly better. Compared with traditional carbon fiber felt and carbon foam, it is a rare rigid thermal insulation material that can be used for a long time above 1600 °C. However, traditional carbon aerogels have a glassy carbon structure, which is brittle and difficult to achieve large-scale preparation. The use of high-strength and tough carbon fibers as reinforcements can significantly improve its mechanical properties and large-scale forming ability through interface microstructure control and other means, so as to realize the integrated function of ultra-high temperature heat insulation and load-bearing, and the obtained lightweight carbon matrix composites The material has great application prospects in thermal protection fields such as aerospace vehicles and their power systems.

However, carbon materials are prone to failure due to oxidation at high temperatures, and it is difficult to meet the performance requirements of new-generation aircraft and their power systems for thermal protection materials in aerobic environments. Modification can effectively improve the anti-oxidation and anti-ablation capabilities of carbon aerogels, and meet the requirements of heat protection, heat insulation and bearing capacity in an aerobic environment. Therefore, the present invention proposes a matrix doping technology suitable for lightweight carbon matrix composites (carbon aerogel composites, carbon foam composites), by introducing one or more ceramic matrixes with anti-oxidation function into the light A carbon aerogel and a ceramic double matrix are formed in the carbon matrix composite material, so as to obtain a lightweight carbon-ceramic composite material with integrated functions of heat protection, heat insulation and load bearing.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a heat-proof-heat-insulation-bearing integrated lightweight carbon-ceramic composite material and a preparation method thereof, so as to meet the thermal protection requirements in an ultra-high temperature aerobic environment.

For achieving the above object, the technical scheme adopted in the present invention is as follows:

A preparation method of a heat-proof-heat-insulation-bearing integrated lightweight carbon-ceramic composite material, comprising the following steps:

(1) The fiber-reinforced lightweight carbon-based composite material is used as the base material and processed into the desired shape, and the surface is cleaned by ultrasonic cleaning with alcohol, and then placed in an oven at 90-120°C for 24-48 hours;

(2) Prepare material A, mix material A with a solvent in a certain proportion, and mechanically stir for 1 to 4 hours to obtain an impregnation solution; the material A is boric acid or phosphoric acid; or, the material A is a ceramic with antioxidant components powder; or, the material A is an organic or inorganic precursor of an antioxidant component; the antioxidant component is one or more of SiBCN, SiCO, SiC, ZrC, ZrB ₂ , HfC and HfB ₂ ; Described solvent is one or more of xylene, ethanol and distilled water;

(3) Immerse the lightweight carbon-based composite material sample into the dipping solution prepared in step (2), and immerse the solution in the light-weight carbon-based composite material sample by ultrasonic vibration, vacuum or normal pressure impregnation and other methods, and evenly distribute it in the lightweight carbon-based composite material sample. After a certain period of time, take out the sample and wipe it dry;

(4) placing the light carbon-based composite material sample impregnated in step (3) in a drying oven to solidify and dry at atmospheric pressure, and then heat the composite material at high temperature to obtain a light carbon-ceramic composite material containing antioxidant components Material; curing and drying process parameters are 80 ~ 170 ℃, heat preservation for 2 ~ 4h;

(5) Repeat the process from step (2) to step (4) 0 to 5 times.

In the above step (1), the density of the lightweight carbon-based composite material ranges from 0.2 to 0.7 g/cm ³ , and the lightweight carbon-based composite material is a fiber-reinforced carbon aerogel composite material or a carbon foam composite material.

In the above step (2), when the material A is boric acid or phosphoric acid, the preparation method of the impregnation solution is as follows: pour the boric acid or phosphoric acid powder into 90° C. deionized water, stir mechanically until most of the powder is dissolved, and then put it into an ultrasonic oscillator Dissolve by ultrasonic vibration at 110° C. to obtain a boric acid or phosphoric acid impregnating solution; wherein: the weight ratio of the amount of boric acid powder or phosphoric acid powder to water is 1:(3-10).

In the above step (2), when the material A is a ceramic powder of anti-oxidation components, the preparation method of the impregnating solution is as follows: pour the ceramic powder into deionized water or ethanol, stir magnetically for 2 to 4 hours, and prepare the ceramic powder Powder impregnation solution; wherein: the weight ratio of the amount of the ceramic powder to the solvent is (5-30):100.

In the above step (2), when the material A is an organic or inorganic precursor of an antioxidant component, the preparation method of the dipping solution is as follows: mixing the precursor of the antioxidant component with xylene in a certain proportion, magnetic stirring After 2 to 4 hours, a precursor impregnation solution is prepared; the weight ratio of the precursor of the antioxidant component to the xylene solvent is (5 to 30): 100; the precursor of the SiBCN is polyborosilazane PSNB, SiCO The precursor is polysiloxane PSO, the SiC precursor is polycarbosilane PCS, the precursor of ZrC is organic zirconium precursor PZC, the precursor of ZrB ₂ is organic zirconium precursor PZB, HfC and HfB ₂ are the precursors of HfCl ₄ is an organic precursor formulated as a hafnium source.

In the above step (3), when the impregnation solution is prepared by using boric acid or phosphoric acid, ultrasonic vibration is used for impregnation, and the impregnation time is 0.5 to 2h; when the impregnation solution is prepared by using ceramic powder or precursor of antioxidant components, Vacuum-normal pressure impregnation is adopted. The specific method is as follows: put the sample into a beaker and place it in a vacuum impregnation tank, evacuate the impregnation tank to a vacuum (vacuum degree ≤-0.1MPa), and use the pressure difference to introduce the precursor impregnation solution into the vacuum impregnation tank. In the beaker of the sample, keep the vacuum degree for 0.5 to 2 hours and then maintain the normal pressure for 0.5 to 2 hours.

In the above step (4), when boric acid or phosphoric acid is used to impregnate the solution, the process of heat-treating the sample is carried out in multiple steps: the temperature is increased from normal temperature to 170-250 ℃ at a heating rate of 5 ℃/min under an inert atmosphere for 0.5-1 h, and then Continue to heat up to 300-400°C for 0.5-1h, then heat up to 500-700°C and hold for 0.5-1h.

In the above step (4), when the impregnation solution is prepared from the ceramic powder or precursor of the anti-oxidation component, the sample heat treatment process is: in the cracking furnace in an inert atmosphere, the temperature is increased to 800～800～ 1500℃, keep warm for 0.5-2h, and cool down naturally under a protective atmosphere.

In the above step (5), when the steps (2) to (4) are repeated, the composition of the modified components of the lightweight carbon-based composite material can be adjusted by changing the concentration of the impregnating solution, the type of the impregnating solution and the order of impregnation. The concentration, type, order of the impregnating solution and the resulting modified composite material include but are not limited to the following 10 kinds:

(1) Impregnation sequence: 25wt.% boric acid solution; obtained material: boron oxide modified lightweight carbon-based composite material;

(2) Impregnation sequence: 25wt.% boric acid solution, 10wt.% PSNB; obtained material: boron oxide-SiBCN modified lightweight carbon-based composite material;

(3) Impregnation sequence: 20 wt.% PSNB; obtained material: SiBCN modified lightweight carbon matrix composite material;

(4) Impregnation sequence: 30 wt.% phosphoric acid solution; obtained material: phosphoric acid-modified light carbon-based composite material;

(5) Impregnation sequence: 25wt.% PCS; obtained material: SiC modified lightweight carbon matrix composite material;

(6) Impregnation sequence: 30 wt.% PSO; obtained material: SiCO precursor modified light carbon matrix composite material;

(7) Impregnation sequence: 15wt.% PZB; obtained material: ZrB ₂ modified light carbon matrix composite material;

(8) Impregnation sequence: 20wt.% PCS, 10wt.% PZC; obtained material: SiC-ZrC modified lightweight carbon matrix composite material;

(9) Impregnation sequence: 10 wt.% PCS, 20 wt.% HfB ₂ organic precursor; obtained material: SiC-HfB ₂ modified lightweight carbon-based composite material;

(10) Impregnation sequence: 10 wt. % PCS, 15 wt. % PZB, 15 wt. % PZC; obtained material: SiC-ZrB ₂ -ZrC modified light carbon matrix composite material.

The prepared integrated lightweight carbon-ceramic composite material is composed of fiber reinforcement, carbon aerogel and ceramic double matrix. The ceramic matrix is uniformly dispersed in the three-dimensional nano-network structure of carbon aerogel. The thermal insulation-bearing and oxidative ablation resistance of the ceramic matrix meet the multi-functional requirements in a long-term high temperature aerobic environment.

The design mechanism of the present invention is as follows:

Using impregnation solutions prepared with different concentrations of antioxidant components (or their precursors), the matrix doping of lightweight carbon matrix composites is carried out by vacuum impregnation, dehydration drying, or ceramic precursor impregnation and pyrolysis (PIP) process; It has the characteristics of good phase fluidity. The prepared solution is introduced into the interior of the aerogel matrix through the pores of the aerogel matrix. Anti-oxidation and ablation performance in high temperature aerobic environment. As a low-temperature antioxidant component, boron/phosphoric acid can form a glass phase oxide after drying and dehydration, which has high viscosity and strong adhesion to the substrate, and can form a protective layer on the inner and outer surfaces; polymer-derived ceramics are used as high-temperature and ultra-high temperature The anti-oxidation component is formed by the high temperature cracking of its precursor solution. It has excellent anti-oxidation and ablation properties, and the temperature resistance can reach more than 2000 ℃. In the present invention, the impregnation solution prepared by selecting single and mixed antioxidant components has good fluidity, and has good wettability and permeability to carbon aerogel materials, and the antioxidant components infiltrated in the nano-carbon network can consume oxygen. And inhibit the diffusion of oxygen, while reducing the contact between the substrate and oxygen, thereby improving the oxidative ablation performance.

The present invention has the following beneficial effects:

1. The present invention adopts ultrasonic vibration and vacuum plus atmospheric impregnation process to introduce boron/phosphoric acid, anti-oxidation ceramic powder and its precursor into the light carbon-based composite material, and obtain carbon aerogel through processes such as curing and heat treatment. -Ceramic dual-matrix composite material significantly improves the overall anti-oxidation and ablation performance of the material, thereby meeting the needs of integrated use of heat-proof-heat-insulation-load bearing in a high-temperature aerobic environment.

2. The method of the present invention can realize the oxidation and ablation resistance of the light carbon matrix composite material in a wide temperature range by changing the type, content and introduction order of the ceramic components. Compared with the lightweight carbon-based composite material, the mechanical and anti-oxidative properties of the material of the present invention are significantly improved, the compressive strength is increased from 62.7 MPa to 90.9 MPa, and the weight loss rate of static oxidation at 1300° C. for 15 minutes is reduced from 14.92% to 9.19%.

Description of drawings

FIG. 1 is a flow chart of a process according to an embodiment of the present invention.

Figure 2 shows the microstructure and morphologies of the lightweight carbon matrix composites before and after doping and after oxidation; in which: (a) before doping; (b) after doping SiBCN ceramics; (c) microscopic morphology after oxidation.

Figure 3 shows the comparison of the oxidation weight loss rate before and after the doping of the light carbon matrix composites.

Figure 4 shows the comparison of the compressive strength of lightweight carbon matrix composites before and after doping.

Detailed ways

In order to further understand the present invention, the present invention will be described below in conjunction with examples, but the examples are only to further illustrate the features and advantages of the present invention, rather than limiting the claims of the present invention.

Since SiBCN ceramics have excellent high temperature stability and wide temperature range oxidation resistance, the following uses SiBCN high temperature ceramics as an anti-oxidative ablation component to perform matrix doping on lightweight carbon matrix composites as an example to further the present invention To help better understand the present invention, FIG. 1 is a process flow diagram, but the protection scope of the present invention is not limited to the embodiments.

Example 1:

This embodiment is the preparation of integrated lightweight carbon-ceramic composite material, and the specific process is as follows:

(1) The lightweight carbon matrix composite material with a density of 0.6 g/ ^cm3 was processed into a block sample with a size of 12.7 × 23.2 × 32.0 mm, and the surface was cleaned by ultrasonic cleaning with alcohol, and then placed in an oven Dry at 120°C for 24h.

(2) Dissolve the organic precursor (PSNB) of SiBCN ceramics in xylene solvent, and mix them thoroughly by magnetic stirring for 2 hours to obtain a PSNB precursor impregnation solution with a concentration of 20%.

(3) put the beaker containing the light carbon-based composite material sample into the vacuum impregnation tank and evacuated it (vacuum degree≤-0.1MPa), and use the pressure difference to introduce the above-mentioned PSNB precursor impregnation solution into the beaker, After maintaining the pressure state for 0.5 hours, the samples were immersed under normal pressure for 0.5 hours, and the samples were taken out and wiped dry.

(4) Put the impregnated sample in a 170°C oven for 2 hours under normal pressure, then put it into a cracking furnace and pass into a protective atmosphere, heat it up to 900°C at a rate of 5°C/min, and keep it for 1 hour to obtain SiBCN modified light quality carbon matrix composites.

(5) Repeat steps (2) to (4) once.

After impregnation with 20% PSNB precursor solution, amorphous SiBCN ceramics are evenly distributed in the porous body of the obtained lightweight carbon matrix composite material, and the weight gain rate is 11.16%; Oxygen, the weight loss rate of the sample after constant temperature oxidation for 15min was 9.19%. Compared with the unimpregnated material, the weight loss rate of the modified and doped composite material decreased by about 38%, and the anti-oxidation performance was significantly improved. Figure 2 shows the microstructure of the material before and after doping and after oxidation, Figure 3 shows the oxidation weight loss rate before and after doping, and Figure 4 shows the compressive strength of the material before and after doping.

Example 2:

The difference from Example 1 lies in the type of dipping solution and the dipping process. In the present invention, the process parameters affecting the antioxidant performance of the lightweight carbon-based composite material are mainly the concentration, type and introduction order of the impregnating solution. Doping is performed to further explain the present invention, and includes the following steps:

(1) The lightweight carbon matrix composite material substrate with a density of 0.4 g/cm ³ was processed into a block sample with a size of 13.1 × 23.0 × 32.5 mm, and the surface was cleaned by ultrasonic cleaning with alcohol, and then placed in an oven Dry at 120°C for 24h.

(2) after pouring the boric acid powder into water and stirring with a glass rod until most of the powder is dissolved, use an ultrasonic instrument to carry out 110 ° C heating and ultrasonic vibration dissolving to obtain a 25% boric acid solution; adopt the same method as (2) in Example 1 to obtain 7% PSNB precursor impregnation solution.

(3) put the beaker containing the light carbon-based composite material sample into the vacuum impregnation tank and evacuated it (vacuum degree≤-0.1MPa), and use the pressure difference to introduce the above-mentioned PSNB precursor impregnation solution into the beaker, After maintaining the pressure state for 0.5 hours, the samples were immersed under normal pressure for 0.5 hours, and the samples were taken out and wiped dry.

(4) Put the impregnated sample in an oven at 170°C for 2 hours under normal pressure, then put it into a cracking furnace and introduce a protective atmosphere, heat it up to 900°C at a rate of 5°C/min, and keep it for 1 hour to obtain SiBCN modification. Lightweight carbon matrix composites.

(5) The samples were then impregnated with boric acid solution, dried at 170 °C for 2 h after impregnation; then dehydrated at 330 °C for 0.5 h under a protective atmosphere to obtain B ₂ O ₃ -SiBCN modified light carbon matrix composites. The sample weight gain rate was 11.38%. B ₂ O ₃ is in the form of molten glass at medium and low temperature, which can effectively isolate oxygen to protect the carbon matrix. SiBCN has excellent anti-oxidative ablation performance at high temperature. The combination of the two can greatly broaden the integration of heat-insulation-load-bearing The oxidation resistance temperature range of carbon matrix composites.

Claims (10)

1. A preparation method of a heat-proof, heat-insulation and load-bearing integrated light carbon-ceramic composite material is characterized by comprising the following steps: the method comprises the following steps:

(1) the fiber-reinforced light carbon-based composite material is used as a base material and processed into a required shape, the surface is cleaned by blowing, ultrasonic cleaning is carried out by using alcohol, and then the material is placed in an oven to be dried for 24-48 h at the temperature of 90-120 ℃;

(2) preparing a material A, mixing the material A and a solvent according to a certain proportion, and mechanically stirring for 1-4 hours to obtain a dipping solution; the material A is boric acid or phosphoric acid; or the material A is ceramic powder of an antioxidant component; or the material A is an organic or inorganic precursor of an antioxidant component; the antioxidant components are SiBCN, SiCO, SiC, ZrC and ZrB₂HfC and HfB₂One or more of the above; the solvent is xylene or ethyl benzeneOne or more of alcohol and distilled water;

(3) immersing a light carbon-based composite material sample into the immersion solution prepared in the step (2), immersing the solution into the light carbon-based composite material sample by adopting methods such as ultrasonic oscillation, vacuum or normal pressure immersion and the like, keeping for a certain time, taking out the sample, and wiping the sample;

(4) placing the light carbon-based composite material sample soaked in the step (3) into a drying oven for curing and drying, and then carrying out high-temperature heat treatment on the composite material to obtain a light carbon-ceramic composite material containing an antioxidant component;

(5) and (5) repeating the processes from the step (2) to the step (4) for 0-5 times.

2. The preparation method of the heat protection-insulation-bearing integrated light carbon-ceramic composite material as claimed in claim 1, wherein the preparation method comprises the following steps: in the step (1), the density range of the light carbon-based composite material is 0.2-0.7 g/cm³The light carbon-based composite material is a fiber-reinforced carbon aerogel composite material or a carbon foam composite material.

3. The preparation method of the heat-proof, heat-insulating and load-bearing integrated light carbon-ceramic composite material as claimed in claim 1, wherein the preparation method comprises the following steps: in the step (2), when the material A is boric acid or phosphoric acid, the preparation method of the dipping solution comprises the following steps: pouring boric acid or phosphoric acid powder into deionized water at 90 ℃, mechanically stirring until most of the powder is dissolved, and then putting the powder into an ultrasonic oscillator for ultrasonic vibration dissolution at 110 ℃ to obtain boric acid or phosphoric acid dipping solution; wherein: the weight ratio of the boric acid powder or the phosphoric acid powder to the water is 1 (3-10).

4. The preparation method of the heat protection-insulation-bearing integrated light carbon-ceramic composite material as claimed in claim 1, wherein the preparation method comprises the following steps: in the step (2), when the material A is ceramic powder of an antioxidant component, the preparation method of the dipping solution comprises the following steps: pouring the ceramic powder into deionized water or ethanol, and mechanically stirring to obtain a ceramic powder impregnation solution; wherein: the weight ratio of the ceramic powder to the solvent is (5-30): 100.

5. The preparation method of the heat-proof, heat-insulating and load-bearing integrated light carbon-ceramic composite material as claimed in claim 1, wherein the preparation method comprises the following steps: in the step (2), when the material A is an organic or inorganic precursor of an antioxidant component, the preparation method of the dipping solution comprises the following steps: mixing the precursor of the antioxidant component with xylene according to a certain proportion, and preparing a precursor dipping solution after magnetically stirring for 2-4 h; wherein the weight ratio of the precursor of the antioxidant component to the xylene solvent is (5-30): 100; the SiBCN precursor is polyborosilazane PSNB, the SiCO precursor is polysiloxane PSO, the SiC precursor is polycarbosilane PCS, and the ZrC precursor is organic zirconium precursors PZC and ZrB₂The precursors of (1) are organic zirconium precursors PZB, HfC and HfB₂The precursor of (A) is HfCl₄An organic precursor formulated for a hafnium source.

6. The preparation method of the heat protection-insulation-bearing integrated light carbon-ceramic composite material as claimed in claim 1, wherein the preparation method comprises the following steps: in the step (3), when the dipping solution is prepared by adopting boric acid or phosphoric acid, ultrasonic vibration dipping is adopted, and the dipping time is 0.5-2 h; when the dipping solution is prepared by adopting ceramic powder or precursor of an antioxidant component, vacuum-normal pressure dipping is adopted, and the specific method comprises the following steps: putting a sample into a beaker, placing the beaker in a vacuum impregnation tank, vacuumizing the impregnation tank (the vacuum degree is less than or equal to-0.1 MPa), introducing an impregnation solution into the beaker filled with the sample by utilizing pressure difference, keeping the vacuum degree for 0.5-2 h, and then keeping the vacuum degree for 0.5-2 h at normal pressure.

7. The preparation method of the heat-proof, heat-insulating and load-bearing integrated light carbon-ceramic composite material as claimed in claim 1, wherein the preparation method comprises the following steps: in the step (4), when the boric acid or phosphoric acid dipping solution is used, the process of heat-treating the sample is carried out in multiple steps: raising the temperature from the normal temperature to 170-250 ℃ at a temperature raising rate of 5 ℃/min under a protective atmosphere, preserving the heat for 0.5-1 h, then continuing raising the temperature to 300-400 ℃, preserving the heat for 0.5-1 h, raising the temperature to 500-700 ℃ and preserving the heat for 0.5-1 h.

8. The preparation method of the heat-proof, heat-insulating and load-bearing integrated light carbon-ceramic composite material as claimed in claim 1, wherein the preparation method comprises the following steps: in the step (4), when the dipping solution is prepared from ceramic powder or precursor of an antioxidant component, the heat treatment process of the sample is as follows: heating to 800-1500 ℃ at the speed of 5 ℃/min under the protective atmosphere, and preserving the heat for 0.5-2 h.

9. The preparation method of the heat-proof, heat-insulating and load-bearing integrated light carbon-ceramic composite material as claimed in claim 4, wherein the preparation method comprises the following steps: in step (5), when steps (2) to (4) are repeated, the composition of the modified component of the light carbon-based composite material can be adjusted by changing the concentration of the impregnation solution, the type of the impregnation solution and the impregnation sequence, and typical concentrations, types, sequences of the impregnation solution and the obtained modified composite material include, but are not limited to, the following 10 types:

(1) and (3) dipping sequence: 25 wt.% boric acid solution; the obtained material is as follows: boron oxide modified light carbon-based composites;

(2) and (3) dipping sequence: 25 wt.% boric acid solution, 10 wt.% PSNB; the obtained material is as follows: boron oxide-SiBCN modified light carbon-based composite material;

(3) and (3) dipping sequence: 20 wt.% PSNB; the obtained material is as follows: SiBCN modified light carbon-based composite material;

(4) and (3) dipping sequence: 30 wt.% phosphoric acid solution; the obtained material is as follows: phosphoric acid modified light carbon-based composite materials;

(5) and (3) dipping sequence: 25 wt.% PCS; the obtained material is as follows: SiC modified light carbon-based composite material;

(6) and (3) dipping sequence: 30 wt.% PSO; the obtained material is as follows: SiCO precursor modified light carbon-based composite material;

(7) and (3) dipping sequence: 15 wt.% PZB; the obtained material is as follows: ZrB₂A modified light carbon-based composite;

(8) and (3) dipping sequence: 20 wt.% PCS, 10 wt.% PZC; the obtained material is as follows: SiC-ZrC modified light carbon-based composite material;

(9) and (3) dipping sequence: 10 wt.% PCS, 20 wt.% HfB₂An organic precursor; the obtained material is as follows: SiC-HfB₂A modified light carbon-based composite;

(10) and (3) dipping sequence: 10wt.% PCS, 15 wt.% PZB, 15 wt.% PZC; the obtained material is as follows: SiC-ZrB₂-a ZrC modified light carbon based composite.

10. A heat-proof, heat-insulating, load-bearing integrated light carbon-ceramic composite material prepared by the method of any one of claims 1 to 9, wherein: the material consists of a fiber reinforcement body, carbon aerogel and a ceramic double-base body, wherein the ceramic base body is uniformly dispersed in a carbon aerogel three-dimensional nano network structure, and the multifunctional requirement under a long-term high-temperature aerobic environment is met by means of heat insulation-bearing of the carbon aerogel and anti-oxidation ablation of the ceramic base body.

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