Solid solution precursor-silicide synergistic infiltration modified C / C composite material and preparation method thereof
By employing a synergistic melt infiltration modification method combining solid fusible organic precursors and silicide powders, the densification and ablation resistance issues of C/C composite materials in the RMI process were resolved, achieving efficient ceramic modification and enhancing the material's erosion resistance and load-bearing capacity.
Patent Information
- Application Number
- CN202511399554.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-28
- Publication Date
- 2025-12-16
AI Technical Summary
In existing RMI processes, C/C composite materials suffer severe mechanical damage, have many residual low-melting-point phases, and have large pores, making it difficult to densify the preforms, which leads to a decrease in ablation resistance.
A synergistic melt infiltration modification method using solid fusible organic precursors and silicide powders was adopted. The precursors were infiltrated into the C/C composite material to form an interface layer by low-temperature heating, and then reacted with silicides at high temperature to generate a uniform ceramic phase, thereby achieving densification.
It shortens the preparation cycle, improves the density and ablation resistance of C/C composite materials, while maintaining good mechanical properties.
Smart Images
Figure CN121135482A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of thermal protection C / C composite matrix modification, specifically relating to a solid solution precursor-silicide synergistic melt infiltration modification of C / C composite material and its preparation method. Background Technology
[0002] Carbon / carbon (C / C) composites are widely used in aerospace thermal structural components, braking systems, and thermal fields due to their high specific strength, high temperature resistance, wear resistance, and excellent high-temperature mechanical properties. However, C / C composites have high oxidizing activity, leading to rapid oxidation in high-temperature aerobic environments and a severe decline in mechanical properties. Ultra-high temperature ceramic-modified C / C composites inherit the oxidation and ablation resistance of ultra-high temperature ceramics while overcoming the inherent brittleness and poor reliability of pure ceramics, making them ideal materials for thermal protection systems in the aerospace field.
[0003] The main preparation methods for ultra-high temperature ceramic-modified C / C composites include precursor impregnation pyrolysis (PIP) and reactive melt infiltration (RMI). PIP has a long preparation cycle, and the resulting composite material has loose ceramic particles that are difficult to resist the strong gas flow during ablation. RMI, due to its short preparation cycle, simple process, and high densification degree, has gradually become the primary technology for the industrial-scale preparation of C / C composite matrix modification. However, during RMI, the high-temperature melt easily erodes the carbon fibers, leading to a decrease in the mechanical properties of the composite material. Furthermore, the residual low-melting-point phase has weak resistance to gas flow erosion, resulting in a decrease in the ablation resistance of the modified composite material. Therefore, improving the mechanical properties of the composite material and reducing the content of low-melting-point phases are among the urgent problems that need to be solved to achieve high-performance composite materials using RMI. Tonghui Wen et al. [Tonghui Wen, Effects of polymer-derived ZiC interlayer on mechanical properties and ablation performance of C / C-ZiC-ZrC-SiC composites prepared by RMI, Journal of the European Ceramic Society, 2024, 44: 5623-5638.] improved the mechanical properties and ablation resistance of ultra-high temperature ceramic-modified C / C composites prepared by RMI by preparing a ZrC / SiC interlayer through process in-processing (PIP). However, this method often requires multiple PIPs to achieve an effective interlayer thickness, increasing the preparation cycle. Furthermore, the evaporation of solvent in the precursor solution makes it difficult to form a dense ceramic layer, thus weakening the protective effect of the interlayer. In addition, the prepared ceramic interlayer slows down the reaction between the high-temperature melt and the carbon matrix in RMI, leading to an increase in the content of residual low-melting-point phases. Meanwhile, for preforms containing large pores, especially 3D fine-knitted puncture preforms, three-dimensional four-dimensional preforms, 3D stitched preforms, and 2.5D woven preforms, large-sized pores exist between layers. This structural feature causes a critical problem of percolation failure during RMI (Regenerative Motion Injection). Due to the excessively large pore volume and insufficient carbon source content within the region, the carbon source cannot fully react with the infiltrator, resulting in an excessive amount of unreacted infiltrator. Under the influence of gravity and capillary forces, the infiltrator flows rapidly along the large pores with low resistance, thus flowing out of the matrix and ultimately making it difficult to achieve effective densification of the matrix. Therefore, how to prepare a dense ultra-high temperature ceramic interface layer while ensuring the infiltrator fully reacts to form a dense matrix is one of the key challenges that urgently needs to be overcome in the preparation of RMI composite materials with both high load-bearing capacity and ablation resistance. Summary of the Invention
[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material and its preparation method, so as to solve the problems of severe mechanical damage, residual low melting point phase, and difficulty in densifying and ceramicizing preforms with large pores in the prior art.
[0005] To achieve the above objectives, the present invention employs the following technical solution: A method for preparing a C / C composite material with synergistic melt infiltration modification by a solid solution precursor and a silicide includes the following steps: S1, a low-density C / C composite material is embedded in a solid fusible organic precursor powder, and heated under vacuum conditions, the solid fusible organic precursor powder melts and penetrates into the low-density C / C composite material to obtain a precursor-modified C / C composite material. S2, mix solid fusible organic precursor powder and silicide powder, heat the mixed powder to obtain solid fusible organic precursor powder encapsulated with silicide, for subsequent synergistic melting and infiltration; S3, the precursor-modified C / C composite material is embedded in a solid fusible organic precursor-encapsulated silicide melt-infiltrating powder to obtain a reaction system. The reaction system is then subjected to high-temperature heat treatment under vacuum conditions to obtain a solid solution precursor-silicide synergistic melt-infiltrating ceramic-modified C / C composite material.
[0006] A further improvement of the present invention is that: Preferably, in S1, the density of the low-density C / C composite material is 1.1~1.5 g / cm³. 3 .
[0007] Preferably, in S1, the low-density C / C composite porous preform is any one of a 3D fine-knitted puncture preform, a three-dimensional four-way preform, a 3D stitched preform, or a 2.5D woven preform.
[0008] Preferably, in S1 and S2, the solid fusible organic precursor is any one or more of zirconium acetylacetonate, hafnium acetylacetonate, titanium acetylacetonate, lanthanum acetylacetonate, lutetium acetylacetonate, zirconium acetate, hafnium(IV) isopropoxide complex, hafnium tetrachloride, and tantalum pentachloride.
[0009] Preferably, in S1, the heating temperature is 200-350 °C and the heating time is 0.5-3 h.
[0010] Preferably, in S2, the silicide is any one or more of silicon, titanium silicide, tantalum silicide, zirconium silicide, or hafnium silicide.
[0011] Preferably, in S2, the heating temperature is 200-350 °C and the heating time is 0.5-3 h.
[0012] Preferably, in S2, the mixing volume ratio of the solid fusible organic precursor powder and the silicide powder is 1:1 to 5:1.
[0013] Preferably, in S3, the high-temperature heat treatment temperature is 1400-1800 °C, and the holding time is 1-3 h.
[0014] A solid solution precursor-silicide synergistic melt infiltration modified C / C composite material prepared by any one of the above preparation methods, wherein the main material of the solid solution precursor-silicide synergistic melt infiltration modified C / C composite material is a C / C composite material, and the C / C composite material contains a solid fusible organic precursor and a silicide-converted carbide ceramic phase.
[0015] Compared with the prior art, the present invention has the following beneficial effects: This invention involves embedding a low-density C / C composite material within a solvent-free solid fusible organic precursor. Under vacuum conditions and low-temperature heating, the organic precursor melts and infiltrates into the C / C composite material, forming an interface layer. Next, the solid fusible organic precursor is mixed with silicide powder and heated to melt the organic precursor and encapsulate the silicide powder. The C / C composite material containing the interface layer is then embedded within the resulting precursor-silicide powder mixture. Synergistic melting and infiltration are achieved under vacuum and high-temperature conditions, thereby preparing a ceramic-modified C / C composite material. This invention offers advantages such as a short production cycle, uniform ceramic phase distribution, complete reaction of the melting and infiltrating agent, and a composite material that combines load-bearing capacity with resistance to erosion and ablation. Attached Figure Description
[0016] Figure 1 This paper describes the reaction mechanism of a solid solution precursor-silicide synergistic melt infiltration modification process for C / C composite materials. Figure (a) shows the evolution of the solid fusible precursor and silicide mixed powder during low-temperature heating. The silicide undergoes no phase or morphological transformation, while the solid fusible precursor gradually melts during low-temperature heating, forming a film that covers the surface of the inorganic silicide powder, forming a shell, and undergoes self-polymerization to generate polymer molecules. Figure (b) shows the evolution of the precursor and silicide mixed powder during high-temperature heating. During heating, the polymer gradually transforms into nano-ceramics that adhere to the silicide surface. As the temperature reaches the silicide's melting point, the silicide gradually melts into a liquid state, and the surface nano-ceramics dissolve into the liquid silicide. Under capillary force, the liquid silicide containing nano-ceramics infiltrates into the C / C composite material and reacts to form a ceramicized composite material.
[0017] Figure 2The XRD patterns are of the ceramic-modified composite materials obtained in Examples 1-4.
[0018] Figure 3 These are macroscopic photographs of the composite materials obtained in Examples 1-4 after plasma ablation. Specifically, Figures (a) and (a1) show the morphology of the material obtained in Example 1 after plasma ablation; Figures (b) and (b1) show the morphology of the material obtained in Example 2 after plasma ablation; Figures (c) and (c1) show the morphology of the material obtained in Example 3 after plasma ablation; Figures (d) and (d1) show the morphology of the material obtained in Example 4 after plasma ablation; Figures (a), (b), (c), and (d) are macroscopic photographs of the surface of the composite material after plasma ablation; and Figures (a1), (b1), (c1), and (d1) are three-dimensional contour photographs and cross-sectional roughness photographs of the composite material after plasma ablation.
[0019] Figure 4 The mechanical properties of the composite materials obtained in Examples 1-4 are shown. Detailed Implementation
[0020] To enable those skilled in the art to understand the features and effects of the present invention, the terms and expressions used in the specification and claims are explained and defined in general below. Unless otherwise specified, all technical and scientific terms used herein have the ordinary meaning understood by those skilled in the art regarding the present invention, and in case of conflict, the definitions in this specification shall prevail.
[0021] In this article, unless otherwise specified, “contains,” “includes,” “containing,” “has,” or similar terms cover the meanings of “composed of” and “mainly composed of,” for example, “A contains a” covers the meanings of “A contains a and others” and “A contains only a.”
[0022] The present invention will be further illustrated below with reference to specific embodiments. It should be understood that these embodiments are for illustrative purposes only and are not intended to limit the scope of the invention. Furthermore, it should be understood that after reading the teachings of this invention, those skilled in the art can make various alterations or modifications to the invention, and these equivalent forms also fall within the scope defined by the appended claims.
[0023] The following examples use instruments and equipment conventional in the art. Experimental methods in the following examples, unless otherwise specified, are generally performed under conventional conditions or as recommended by the manufacturer. All raw materials used in the following examples are conventional commercially available products with specifications conventional in the art. In this specification and the following examples, unless otherwise specified, "%" refers to weight percentage, "parts" refers to parts by weight, and "ratio" refers to weight proportion.
[0024] This invention discloses a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material and its preparation method, comprising the following steps: S1, low-density C / C composite material is embedded in solid fusible organic precursor powder, and the solid fusible precursor is melted and infiltrated into the C / C composite material by low-temperature heating under vacuum conditions. S2, mix solid fusible organic precursor and silicide powder, and heat the mixed powder at low temperature to melt the organic precursor and encapsulate the silicide powder; S3, the C / C composite material obtained in S1 is embedded in the precursor-silicide powder obtained in S2 to obtain a reaction system. The reaction system is then subjected to synergistic melting and infiltration under vacuum and high temperature conditions to obtain ceramic-modified C / C composite material.
[0025] In the preparation method of this invention, in S1, a solid fusible organic precursor is first infiltrated into a C / C composite material through low-temperature heating. During this process, the solid fusible precursor gradually melts during the low-temperature heating and, under vacuum conditions, infiltrates into the C / C composite material due to capillary forces to form an interface layer. Furthermore, the precursor undergoes a self-polymerization reaction to form polymer molecules. In S2, the solid fusible organic precursor and silicide powder are first mixed. The organic powder is adsorbed onto the surface of the inorganic silicide powder, forming a layer as shown in the diagram. Figure 1 The coating shown in Figure (a) is then formed into a solid fusible organic precursor through low-temperature heating. During this process, the silicide undergoes no phase or morphological transformation; the solid fusible precursor gradually melts during low-temperature heating and undergoes a self-polymerization reaction to form a polymer of carbides, which melts into a film covering the surface of the inorganic silicide powder to form a shell. See Figure (s3) for details. Figure 1 In Figure (b), under high temperature and vacuum conditions, the polymer gradually transforms into nano-ceramic powder that adheres to the surface of the silicide powder. As the temperature reaches the melting point of the silicide, the silicide gradually melts into a liquid state and flows. The nano-ceramic powder on the surface dissolves into the liquid silicide. Under the action of capillary force, the precursor transforms into nano-ceramic powder and penetrates into the interior of the composite material along with the high temperature melt to produce a ceramicization reaction, thereby obtaining a ceramic-modified C / C composite material.
[0026] In some embodiments of the present invention, in S1, the density of the C / C composite material is 1.1~1.5 g / cm³. 3 C / C composite porous preforms include 3D fine-knitted puncture preforms, three-dimensional four-way preforms, 3D stitched preforms, and 2.5D woven preforms.
[0027] In some embodiments of the present invention, the mixing process in S2 is carried out by stirring or mixing with a powder mixer.
[0028] In some embodiments of the present invention, in S1 and S2, the solid fusible organic precursor is any one or more of zirconium acetylacetonate, hafnium acetylacetonate, titanium acetylacetonate, lanthanum acetylacetonate, lutetium acetylacetonate, zirconium acetate, hafnium(IV) isopropoxide complex, hafnium tetrachloride, and tantalum pentachloride.
[0029] In some embodiments of the present invention, in S1 and S2, the temperature of the low-temperature heating is 200-350 °C, and the heating time is 0.5-3 h.
[0030] In some embodiments of the present invention, in S2, the silicide is any one or more of silicon, titanium silicide, tantalum silicide, zirconium silicide, or hafnium silicide.
[0031] In some embodiments of the present invention, in S2, the mixing volume ratio of the solid fusible organic precursor powder and the infiltrator powder is 1:1-5:1.
[0032] In some embodiments of the present invention, in S3, the temperature of the high-temperature heat treatment is 1400-1800 °C, and the holding time is 1-3 h.
[0033] A second aspect of this invention discloses a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material obtained by the above preparation method. The main material of this composite material is a C / C composite material, in which a solid fusible organic precursor and a silicide-converted carbide ceramic phase are distributed. This method infiltrates the nano-ceramic phase of the solid fusible organic precursor into the interior of the C / C composite material through silicide, thereby enabling uniform modification of the interior of the C / C composite material.
[0034] The following description, in conjunction with specific embodiments, provides further details.
[0035] Example 1 (1) The density is 1.3 g / cm³ 3 2.5D needled C / C composite material was embedded in zirconium acetylacetonate, heated to 200 °C under vacuum and held for 2 h to obtain precursor-modified C / C composite material. (2) Silicon, zirconium silicide powder, and zirconium acetylacetonate are mixed, wherein the mass ratio of silicon powder to zirconium silicide powder is approximately 1:2-1:1, and the volume ratio of precursor to silicide is 1:1. The organic precursor powder is adsorbed onto the surface of the inorganic silicide powder. The mixed powder is heated to 200 °C and held for 2 h. The solid, fusible zirconium acetylacetonate precursor gradually melts and undergoes a self-polymerization reaction to generate zirconium carbide polymer. Therefore, a silicide powder coated with a solid polymer film is obtained, such as... Figure 1 As shown.
[0036] (3) The modified C / C composite material was embedded in the precursor-silicide powder and heat-treated under vacuum at 1600 °C for 2 h. During the heating process, the zirconium carbide polymer gradually decomposed into nano-sized zirconium carbide ceramic powder and attached to the surface of the inorganic powder. As the temperature reached the melting point of the silicide, the silicide gradually melted into a liquid flow. The zirconium carbide nano-ceramics on the surface dissolved into the molten silicide. Under the action of gravity and capillary force, the zirconium carbide nanoparticles infiltrated into the C / C composite material along with the silicide and reacted with the matrix to transform into zirconium carbide and silicon carbide ceramics. Then, the C / C-ZrC-SiC ceramic matrix composite material was obtained by cooling.
[0037] Example 2 (1) 1.3 g / cm 3 2.5D needled C / C composite material was embedded in zirconium acetylacetonate, heated to 260 °C under vacuum and held for 2 h to obtain precursor-modified C / C composite material. (2) Silicon, zirconium silicide powder and zirconium acetylacetonate were mixed, wherein the mass ratio of silicon powder to zirconium silicide powder was approximately 1:2-1:1, and the volume ratio of precursor to silicide was 2:1. The mixed powder was heated to 260 °C and kept at that temperature for 2 h to obtain precursor-coated silicide powder; (3) The modified C / C composite material was embedded in the precursor-silicide powder, heat-treated at 1600 °C under vacuum for 2 h, and then cooled to obtain C / C-ZrC-SiC ceramic matrix composite material.
[0038] Example 3 (1) 1.3 g / cm 3 2.5D needled C / C composite material was embedded in zirconium acetylacetonate, heated to 280 °C under vacuum and held for 2 h to obtain precursor-modified C / C composite material. (2) Silicon, zirconium silicide powder and zirconium acetylacetonate were mixed, wherein the mass ratio of silicon powder to zirconium silicide powder was approximately 1:2-1:1, and the volume ratio of precursor to silicide was 3:1. The mixed powder was heated to 280 °C and kept at that temperature for 2 h to obtain precursor-coated silicide powder; (3) The modified C / C composite material was embedded in the precursor-silicide powder, heat-treated at 1600 °C under vacuum for 2 h, and then cooled to obtain C / C-ZrC-SiC ceramic matrix composite material.
[0039] Example 4 (1) 1.3 g / cm 32.5D needled C / C composite material was embedded in zirconium acetylacetonate, heated to 300 °C under vacuum and held for 2 h to obtain precursor-modified C / C composite material. (2) Silicon, zirconium silicide powder and zirconium acetylacetonate were mixed, wherein the mass ratio of silicon powder to zirconium silicide powder was approximately 1:2-1:1, and the volume ratio of precursor to silicide was 4:1. The mixed powder was heated to 300 °C and kept at that temperature for 2 h to obtain precursor-coated silicide powder; (3) The modified C / C composite material was embedded in the precursor-silicide powder, heat-treated at 1600 °C under vacuum for 2 h, and then cooled to obtain C / C-ZrC-SiC ceramic matrix composite material.
[0040] See Figure 2 The figures show the XRD patterns of the ceramic-modified composite materials obtained in Examples 1-4. As can be seen from the figures, with the increase in the ratio of precursor to silicide, the residual zirconium silicide in the composite material gradually decreases or even disappears, while the proportion of ZrC in the composite material gradually increases.
[0041] Figure 3 These are macroscopic photographs of the composite materials obtained in Examples 1-4 after plasma ablation. As can be seen from the figures, with an increasing ratio of precursor to silicide, when the precursor content is low, the remaining zirconium silicide makes it difficult to resist airflow erosion, resulting in poor ablation resistance. The mass ablation rate is 3.27 mg / s, and the linear ablation rate is only 25.77 μm / s. With an increasing precursor ratio, the zirconium silicide content decreases, and the zirconium silicide is converted to zirconium carbide and silicon carbide, improving the ablation resistance. When the precursor to silicide ratio is 2:1, the mass ablation rate of the resulting composite material is -0.34 mg / s, and the linear ablation rate is only 0.14 μm / s. When the precursor ratio is too high, the increased proportion of ZrC and decreased proportion of SiC in the composite material leads to a decrease in thermal conductivity, resulting in a higher response temperature exceeding the melting point of zirconium oxide, thus deteriorating the plasma ablation resistance of the composite material.
[0042] Figure 4 The figures show the mechanical properties of the composite materials obtained in Examples 1-4. As can be seen from the figures, the mechanical properties of the composite materials first increase and then decrease with increasing precursor-to-silicide ratio. When the precursor content is low, the resulting composite material contains more residual brittle zirconium silicide, resulting in a flexural strength of 170.7 MPa. When the precursor ratio is too high, the reaction between the oxygen-containing components and carbon in the precursor leads to erosion of the carbon-containing matrix, resulting in decreased mechanical properties. When the volume ratio of precursor to silicide is 2:1, the residual brittle zirconium silicide is low, and the erosion of carbon by the oxygen-containing components in the precursor is weak, resulting in the best mechanical properties, reaching a maximum of 207.5 MPa.
[0043] Example 5 (1) 1.2 g / cm 3 The 3D puncture C / C composite material was embedded in zirconium acetylacetonate and lanthanum acetylacetonate, wherein the mass ratio of zirconium acetylacetonate to lanthanum acetylacetonate was 10:1. The mixture was heated to 350 °C under vacuum and held for 0.5 h to obtain the precursor-modified C / C composite material. (2) Zirconium silicide powder, zirconium acetylacetonate, and lanthanum acetylacetonate were mixed, wherein the mass ratio of zirconium acetylacetonate to lanthanum acetylacetonate was 10:1, and the volume ratio of precursor to silicide was 5:1. The mixed powder was heated to 350 °C and held at that temperature for 0.5 h to obtain precursor-coated silicide powder; (3) The modified C / C composite material was embedded in the precursor-silicide powder, heat-treated at 1800 °C under vacuum for 2 h, and then cooled to obtain lanthanum-modified C / C-ZrC-SiC ceramic matrix composite material.
[0044] Example 6 (1) 1.2 g / cm 3 The 3D puncture C / C composite material was embedded in zirconium acetylacetonate and tantalum pentachloride, wherein the mass ratio of zirconium acetylacetonate and tantalum pentachloride was 4:1. The mixture was heated to 270 °C under vacuum and held for 2 h to obtain the precursor-modified C / C composite material. (2) Zirconium silicide powder, zirconium acetylacetonate, and tantalum pentachloride were mixed, wherein the mass ratio of zirconium acetylacetonate to tantalum pentachloride was 4:1, and the volume ratio of precursor to silicide was 2:1. The mixed powder was heated to 270 °C and kept at that temperature for 2 h to obtain precursor-coated silicide powder; (3) The modified C / C composite material was embedded in the precursor-silicide powder, heat-treated at 1800 °C under vacuum for 2 h, and then cooled to obtain C / C-ZrC-SiC ceramic matrix composite material.
[0045] Example 7 (1) 1.3 g / cm 3 3D needled C / C composite material was embedded in zirconium acetylacetonate, heated to 300 °C under vacuum conditions and held for 3 h to obtain precursor-modified C / C composite material. (2) Silicon, zirconium silicide powder and zirconium acetylacetonate were mixed, wherein the mass ratio of silicon powder to zirconium silicide powder was approximately 1:2-1:1, and the volume ratio of precursor to silicide was 3:1. The mixed powder was heated to 300 °C and kept at that temperature for 3 h to obtain precursor-coated silicide powder; (3) The modified C / C composite material was embedded in the precursor-silicide powder, heat-treated at 1400 °C under vacuum for 3 h, and then cooled to obtain C / C-ZrC-SiC ceramic matrix composite material.
[0046] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A method for preparing a C / C composite material with synergistic melt infiltration modification by a solid solution precursor and a silicide, characterized in that, Includes the following steps: S1, a low-density C / C composite material is embedded in a solid fusible organic precursor powder, and heated under vacuum conditions, the solid fusible organic precursor powder melts and penetrates into the low-density C / C composite material to obtain a precursor-modified C / C composite material. S2, mix solid fusible organic precursor powder and silicide powder, heat the mixed powder to obtain solid fusible organic precursor powder encapsulated with silicide, for subsequent synergistic melting and infiltration; S3, the precursor-modified C / C composite material is embedded in a solid fusible organic precursor-encapsulated silicide melt-infiltrating powder to obtain a reaction system. The reaction system is then subjected to high-temperature heat treatment under vacuum conditions to obtain a solid solution precursor-silicide synergistic melt-infiltrating ceramic-modified C / C composite material.
2. The method for preparing a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material according to claim 1, characterized in that, In S1, the density of the low-density C / C composite material is 1.1~1.5 g / cm³. 3 .
3. The method for preparing a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material according to claim 1, characterized in that, In S1, the low-density C / C composite porous preform is any one of a 3D fine-knitted puncture preform, a three-dimensional four-way preform, a 3D stitched preform, or a 2.5D woven preform.
4. The method for preparing a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material according to claim 1, characterized in that, In S1 and S2, the solid fusible organic precursor is any one or more of zirconium acetylacetonate, hafnium acetylacetonate, titanium acetylacetonate, lanthanum acetylacetonate, lutetium acetylacetonate, zirconium acetate, hafnium(IV) isopropoxide complex, hafnium tetrachloride, and tantalum pentachloride.
5. The method for preparing a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material according to claim 1, characterized in that, In S1, during the heating process, the heating temperature is 200-350 °C and the heating time is 0.5-3 h.
6. The method for preparing a solid fusible precursor-silicide synergistic infiltration ceramic modification C / C composite material according to claim 1, characterized in that, In S2, the silicide is any one or more of silicon, titanium silicide, tantalum silicide, zirconium silicide, or hafnium silicide.
7. The method for preparing a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material according to claim 1, characterized in that, In S2, the heating temperature is 200-350 °C and the heating time is 0.5-3 h.
8. The method for preparing a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material according to claim 1, characterized in that, In S2, the mixing volume ratio of the solid fusible organic precursor powder and the silicide powder is 1:1-5:
1.
9. The method for preparing a solid solution precursor-silicide synergistic melt infiltration modified C / C composite material according to claim 1, characterized in that, In S3, the high-temperature heat treatment temperature is 1400-1800 °C, and the holding time is 1-3 h.
10. A C / C composite material with synergistic melt infiltration modification by a solid solution precursor and silicide prepared by the preparation method according to any one of claims 1-9, characterized in that, The main material of the solid solution precursor-silicide synergistic melt infiltration modified C / C composite material is a C / C composite material, in which a solid fusible organic precursor and a silicide-converted carbide ceramic phase are distributed.