Lightweight heat-resistant and heat-insulating integrated ceramic composite material and preparation method thereof

Abstract

The present application relates to the technical field of ceramic composite material, and discloses a light heat-proof and heat-insulation integrated ceramic composite material and a preparation method, which comprises the following steps: designing the thickness of a core layer, the thickness of an upper surface layer and the thickness of a lower surface layer, and a material system, wherein the thickness of the upper surface layer is greater than that of the lower surface layer; preparing a ceramic composite material preform; preparing an aerogel composite material, wherein the ceramic composite material preform is dried by supercritical drying; performing hydrophobization treatment on the treated ceramic composite material preform, immersing the ceramic composite material preform in an ethyl silicate solution, and then performing high-temperature treatment after taking out; clamping the treated ceramic composite material preform with a mold, immersing it in modified silica sol, and then solidifying, repeating the immersion and solidification for 3-5 times; pyrolyzing and sintering the treated preform under vacuum, and cooling to room temperature to obtain the light heat-proof and heat-insulation integrated ceramic composite material. The preparation period is shortened, and the preparation efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of ceramic composite materials technology, and in particular, to a lightweight integrated heat-resistant and heat-insulating ceramic composite material and its preparation method. Background Technology

[0002] High-speed spacecraft such as space shuttles and recoverable satellites fly at high speeds for extended periods in the atmosphere, where temperatures over large areas exceed 600°C, and in some cases reach 1400°C. To prevent damage to internal equipment from these high temperatures, highly efficient heat-insulating materials must be used. Ceramic heat-insulating tiles played a crucial role in the US space shuttle and appear to be a mature technology, but they possess inherent limitations such as brittleness (toughness typically 1–5 MPa × m1 / 2), low strength (flexural strength typically less than 5 MPa), relatively high thermal conductivity (typically greater than 0.06 W / m × K), and small single-piece area (typically 200 × 200 mm). These limitations prevent them from adequately meeting the high reliability and efficiency requirements of large-area heat insulation for high-speed spacecraft.

[0003] Based on this, in the prior art, Chinese invention patent CN112094130A proposes a high-temperature resistant, heat-insulating sandwich structure ceramic matrix composite material. This composite material has significant advantages such as good toughness, high strength, and good overall molding performance. Building upon aerogel composite materials and inorganic fiber-reinforced oxide ceramic composite materials, it utilizes the former's low thermal conductivity and high toughness, and the latter's high strength, high toughness, and ablation resistance. A thin layer of high-temperature resistant inorganic fiber-reinforced oxide ceramic composite material is integrally laminated onto both sides of the aerogel composite material, resulting in a new generation of sandwich structure ceramic composite materials. This significantly improves its toughness, panel strength, thermal conductivity, single-piece size, and installation methods. However, in this technology, the preparation of the aerogel composite material and the sandwich structure ceramic composite material are carried out separately during the preform composite process. The mold sizes involved cannot be standardized, and multiple sets of molds of different sizes are often required to prepare one product, followed by separate processing and lamination. This results in complex processes, long preparation cycles, low production efficiency, and high production costs. Summary of the Invention

[0004] This invention provides a lightweight integrated heat-resistant and heat-insulating ceramic composite material and its preparation method, in order to solve the technical problems of long preparation time and high production cost of heat-resistant and heat-insulating composite materials in the prior art.

[0005] According to one aspect of the present invention, a method for preparing a lightweight integrated heat-insulating ceramic composite material is provided, comprising the following steps: S1, designing the core layer thickness, upper surface layer thickness, and lower surface layer thickness, as well as the material system, wherein the upper surface layer thickness is greater than the lower surface layer thickness; S2, preparing a ceramic composite material preform according to the design in step S1; S3, preparing an aerogel composite material by supercritical drying of the ceramic composite material preform; S4, subjecting the ceramic composite material preform treated in step S3 to hydrophobic treatment by immersing the ceramic composite material preform in a tetraethyl orthosilicate solution, and then treating it at high temperature; S5, clamping the ceramic composite material preform treated in step S4 with a mold, immersing it in modified silica sol, and then curing it, repeating the immersion and curing process 3 to 5 times; S6, pyrolyzing and sintering the preform treated in step S5 under vacuum conditions, and cooling it to room temperature to obtain a lightweight integrated heat-insulating ceramic composite material.

[0006] Furthermore, the hydrophobication treatment in step S4 is carried out at a temperature of 30–100°C for a time of 30–120 min.

[0007] Furthermore, in step S5, the impregnation is performed under normal pressure at a temperature of 50–200°C.

[0008] Furthermore, in step S5, the curing temperature is 100–400°C.

[0009] Furthermore, in step S6, the pyrolysis firing temperature is 700–1200°C, and the time is 10–40 min.

[0010] Furthermore, in step S2, the thickness of at least one of the core layer thickness, upper surface layer thickness, and lower surface layer thickness is controllable when preparing the ceramic composite preform.

[0011] Furthermore, in step S2, a ceramic composite material preform is prepared, and the material system is adjustable.

[0012] Furthermore, the thickness of the core layer is 20-300 mm; and / or the thickness of the upper surface layer is 2.0-5.0 mm; and / or the thickness of the lower surface layer is 0.3-1.0 mm.

[0013] Furthermore, the core layer is an aerogel composite material with a porous ceramic structure; the upper surface layer is an oxide fiber ceramic matrix composite material, serving as the hot surface; and the lower surface layer is an oxide fiber ceramic matrix composite material, serving as the cold surface.

[0014] According to another aspect of the present invention, a lightweight heat-insulating integrated ceramic composite material is also provided, which is prepared by the above-described method for preparing the lightweight heat-insulating integrated ceramic composite material.

[0015] The present invention has the following beneficial effects:

[0016] This invention discloses a method for preparing a lightweight integrated heat-resistant and heat-insulating ceramic composite material. The ceramic composite preform adopts a sandwich structure consisting of an upper surface layer (hot surface), a core layer, and a lower surface layer (cold surface). Since the thickness of the upper surface layer (hot surface) and the lower surface layer (cold surface) affects the heat-resistant and heat-insulating performance of the material, the upper surface layer is designed to be thicker to undertake the heat-resistant task and withstand continuous high-temperature environments. The combination of the core layer and the hot surface layer has excellent heat resistance and heat insulation effects. Heat and temperature are significantly reduced by the time they reach the cold surface layer, improving the overall heat-resistant and heat-insulating performance. Simultaneously, the lower surface layer can be bonded to the cabin body during product application. This preform's structural design significantly improves the long-term high-temperature resistance of the lightweight integrated heat-resistant and heat-insulating ceramic composite material, significantly enhancing the heat-resistant and heat-insulating effect of the ceramic composite material and improving the safety performance of the aircraft.

[0017] The present invention discloses a method for preparing a lightweight integrated heat-insulating ceramic composite material. First, based on the thickness design requirements of each upper surface layer (hot surface), core layer, and lower surface layer (cold surface), as well as the design of the material system, a preform of the ceramic composite material is prepared. During the composite process, only one mold is needed to control the thickness and shape, simplifying the preform preparation process and reducing production costs. The prepared ceramic composite preform is then subjected to supercritical drying, hydrophobication treatment, repeated impregnation, and curing. Finally, it is pyrolyzed and sintered under vacuum conditions and cooled to room temperature to obtain the lightweight integrated heat-insulating ceramic composite material. The entire process effectively shortens the preparation cycle, improves preparation efficiency, and is simple to operate, showing great promise for large-scale production of ceramic matrix composite materials in the industrial field.

[0018] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0019] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0020] Figure 1 This is a flowchart of a preferred embodiment of the preparation method of a lightweight heat-resistant and heat-insulating integrated ceramic composite material of the present invention;

[0021] Figure 2 It is a preform of the lightweight heat-resistant and heat-insulating integrated ceramic composite material provided by the present invention;

[0022] Figure 3 The present invention provides a lightweight, heat-resistant, and heat-insulating integrated ceramic composite material. Detailed Implementation

[0023] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0024] Figure 1 This is a flowchart of a preferred embodiment of the preparation method of a lightweight heat-resistant and heat-insulating integrated ceramic composite material of the present invention; Figure 2 It is a preform of the lightweight heat-resistant and heat-insulating integrated ceramic composite material provided by the present invention; Figure 3 The present invention provides a lightweight, heat-resistant, and heat-insulating integrated ceramic composite material.

[0025] like Figure 1 As shown in this embodiment, a lightweight integrated thermal insulation ceramic composite material is first designed as a preform of the ceramic composite material. The preform has a sandwich structure, including a core layer, an upper surface layer, and a lower surface layer. A porous ceramic aerogel composite material is used as the core layer to obtain better thermal insulation performance. An oxide fiber ceramic matrix composite material is used as the hot surface (upper surface layer) and the cold surface (lower surface layer). The thickness of the upper surface layer is greater than that of the lower surface layer because the thickness affects the thermal insulation performance of the material. The upper surface layer is designed to be thicker to undertake the thermal insulation task and withstand the continuous high temperature environment. The combination of the core layer and the hot surface layer has a good heat resistance and thermal insulation effect. The heat and temperature are significantly reduced when they reach the cold surface layer, which can improve the overall thermal insulation performance. At the same time, the lower surface layer can be bonded to the cabin body during product application. In summary, the structure significantly improves the long-term high temperature resistance of the lightweight and low-cost integrated thermal insulation ceramic composite material of the present invention, which can significantly improve the thermal insulation effect of the ceramic composite material and improve the safety performance of the aircraft. Next, the aerogel composite material is prepared. The core layer material is prepared using a supercritical drying method (referring to the methods disclosed in Chinese patents 200510031952.0, 200710034510.0, 201110110844.8, 201110110947.4, 201110110946.X, 201010300112.0, or 201010148105.3). Finally, a lightweight, low-cost integrated heat-resistant and heat-insulating ceramic composite material is obtained. Optionally, the thickness of the core layer is 20-300 mm; the thickness of the upper surface layer is 2.0-5.0 mm; and the thickness of the lower surface layer is 0.3-1.0 mm.

[0026] This invention also provides a method for preparing the above-mentioned lightweight heat-resistant and heat-insulating integrated ceramic composite material, comprising:

[0027] S1. Design the thickness and material system of the core layer, upper surface layer, and lower surface layer;

[0028] S2. Preparation of ceramic composite preforms with controllable thickness and adjustable system (e.g., Figure 2 (as shown);

[0029] S3: Preparation of aerogel composite materials, wherein the ceramic composite material preform is prepared by supercritical drying (refer to the methods disclosed in Chinese Patents 200510031952.0, 200710034510.0, 201110110844.8, 201110110947.4, 201110110946.X, 201010300112.0 or 201010148105.3);

[0030] S4: The ceramic composite preform treated by S3 is subjected to hydrophobic treatment. The ceramic composite preform is immersed in tetraethyl orthosilicate solution for hydrophobic treatment, and then subjected to high temperature treatment after removal.

[0031] S5: Clamp the preform described in S4 with a mold, immerse it in the modified silica sol, and then cure it. Repeat the immersion and curing process 3 to 5 times. The modified silica sol is made by modifying commercially available silica sol (increasing its concentration) to improve the impregnation efficiency of the material.

[0032] S6: Under vacuum conditions, the preform treated in step S5 is subjected to pyrolysis sintering and cooled to room temperature to obtain a lightweight, heat-insulating integrated ceramic composite material (such as...). Figure 3 (As shown).

[0033] Through the design in step S1, the thickness and material system of the core layer, upper surface layer, and lower surface layer are controlled. In step S2, a set of molds is used to fabricate the ceramic composite preform according to the design in step S1, and appropriate pressing is employed. Furthermore, the overall thickness of the ceramic composite preform is controlled through the mold, thereby obtaining the ceramic composite preform (e.g., ...). Figure 2 (As shown).

[0034] like Figure 3 As shown, the lightweight heat-resistant and heat-insulating integrated ceramic composite material prepared by the method of the present invention has a density gradient and has a dense layer and a porous layer.

[0035] Optionally, the hydrophobication treatment temperature in step S4 is 30–100℃, and the time is 30–120 min. If the hydrophobication treatment temperature exceeds 100℃, the solution is prone to evaporation, resulting in poor hydrophobicity. In step S4, the impregnation is performed at room temperature and pressure. The preparation method of this invention does not require sophisticated equipment; room temperature and pressure impregnation is sufficient to achieve the preparation process, meeting the requirements and simplifying the process. In step S5, the impregnation is performed at room temperature and pressure. The preparation method of this invention does not require sophisticated equipment; room temperature and pressure impregnation is sufficient to achieve the preparation process, meeting the requirements and simplifying the process. The curing temperature is 100–400℃. Curing temperatures above 400℃ easily generate bubbles, leading to porous materials; curing temperatures below 100℃ make curing difficult. In step S6, the pyrolysis firing temperature is 700-1200℃ and the time is 10-40 min. If the pyrolysis firing temperature is higher than 1200℃, bubbles are easily generated, resulting in porous materials and damage to fibers. If the pyrolysis firing temperature is lower than 700℃, it is not easy to pyrolyze and fire.

[0036] Example 1

[0037] This embodiment provides a preparation process for a lightweight integrated heat-insulating ceramic composite material. First, a ceramic composite preform is designed. The ceramic composite preform has a sandwich structure, including a core layer, an upper surface layer, and a lower surface layer. The core layer, upper surface layer, and lower surface layer are connected by silica fiber bundle puncture lines. The core layer is silica fiber felt, and the upper and lower surface layers are silica fiber cloth. The thickness of the core layer is 20 mm, the thickness of the upper surface layer is 3.0 mm, and the thickness of the lower surface layer is 0.5 mm. The ceramic composite preform is prepared by supercritical drying (refer to the methods disclosed in Chinese Patents 200510031952.0, 200710034510.0, 201110110844.8, 201110110947.4, 201110110946.X, 201010300112.0, or 201010148105.3); the treated ceramic composite preform is then subjected to hydrophobic treatment at atmospheric pressure. The ceramic composite preform was impregnated in tetraethyl orthosilicate solution at a hydrophobicity treatment temperature of 100°C for 30 minutes. The preform was then clamped in a mold and impregnated in modified silica sol, followed by curing. This impregnation and curing process was repeated three times at a curing temperature of 100°C. Under vacuum conditions, the preform was subjected to pyrolysis sintering at a temperature of 1200°C for 10 minutes, followed by cooling to room temperature. This yielded a lightweight, heat-insulating integrated ceramic composite material.

[0038] The basic properties of the lightweight integrated heat-resistant and heat-insulating ceramic composite material in Example 1 are as follows:

[0039] (1) The thickness of the lightweight heat-resistant and heat-insulating integrated ceramic composite material is 20mm and the density is 0.60g / cm3;

[0040] (2) The room temperature fracture compressive strain of the lightweight heat-resistant and heat-insulating integrated ceramic composite material is 5000με, the tensile strength is 150MPa, and the flexural strength is 200MPa.

[0041] (3) The lightweight heat-resistant and heat-insulating integrated ceramic composite material has a room temperature thickness direction compression of 0.2 MPa to a deformation of 0.3%;

[0042] (4) The lightweight heat-resistant and heat-insulating integrated ceramic composite material prepared in this embodiment was subjected to a quartz lamp single-sided radiation heating test at 1500℃ for 1 hour. After the test, the surface structure of the lightweight heat-resistant and heat-insulating integrated ceramic composite material was intact and there was no obvious damage, indicating that the material system can be used normally for a long time at 1500℃, and the back temperature is 500℃.

[0043] Compared to the high-temperature resistant, heat-insulating sandwich-structure ceramic matrix composite material obtained after implementation of CN112094130A, the preparation method of the lightweight heat-insulating integrated ceramic composite material provided in this embodiment has a shorter preparation cycle (only 3 impregnation and curing cycles). The lightweight heat-insulating integrated ceramic composite material exhibits significant performance improvements in room temperature fracture compressive strain (increased to 5000 με), tensile strength (increased to 150 MPa), flexural strength (increased to 200 MPa), and 0.2 MPa compression set (compression set decreased to 0.3%). The typical ballistic heating environment heat resistance temperature is increased to 1500℃.

[0044] Example 2

[0045] This embodiment provides a preparation process for a lightweight integrated heat-insulating ceramic composite material. First, a ceramic composite preform is designed. The ceramic composite preform has a sandwich structure, including a core layer, an upper surface layer, and a lower surface layer. The core layer, upper surface layer, and lower surface layer are connected by silica fiber bundle puncture lines. The core layer is silica fiber felt, and the upper and lower surface layers are silica fiber cloth. The thickness of the core layer is 25 mm, the thickness of the upper surface layer is 4.0 mm, and the thickness of the lower surface layer is 1 mm. The ceramic composite preform is prepared by supercritical drying (refer to the methods disclosed in Chinese Patents 200510031952.0, 200710034510.0, 201110110844.8, 201110110947.4, 201110110946.X, 201010300112.0, or 201010148105.3); the treated ceramic composite preform is then subjected to… The preform was subjected to hydrophobic treatment by immersion in a tetraethyl orthosilicate solution at atmospheric pressure at a temperature of 30°C for 120 minutes. The preform was then clamped in a mold and immersed in a modified silica sol, followed by curing. This process was repeated five times at a curing temperature of 400°C. Under vacuum conditions, the preform was subjected to pyrolysis sintering and cooled to room temperature at a temperature of 700°C for 40 minutes to obtain a lightweight integrated thermal insulation ceramic composite material.

[0046] The basic properties of the lightweight integrated heat-resistant and heat-insulating ceramic composite material in Example 2 are as follows:

[0047] (1) The thickness of the lightweight heat-resistant and heat-insulating integrated ceramic composite material is 25mm and the density is 0.58g / cm3;

[0048] (2) The room temperature fracture compressive strain of the lightweight heat-resistant and heat-insulating integrated ceramic composite material is 5000με, the tensile strength is 140MPa, and the flexural strength is 200MPa.

[0049] (3) The room temperature thickness direction compression deformation of the lightweight heat-insulating integrated ceramic composite material is 0.5% at 0.2 MPa.

[0050] (4) The lightweight heat-resistant and heat-insulating integrated ceramic composite material prepared in this embodiment was subjected to a quartz lamp single-sided radiation heating test at 1500℃ for 1 hour. After the test, the surface structure of the material was intact and there was no obvious damage, indicating that the material system can be used normally at 1500℃ for a long time, and the back temperature was 520℃.

[0051] Compared to the high-temperature resistant, heat-insulating sandwich-structure ceramic matrix composite material obtained after implementation of CN112094130A, the preparation method of the lightweight heat-insulating integrated ceramic composite material provided in this embodiment has a shorter preparation cycle (only 5 impregnation and curing cycles). The material exhibits significant performance improvements in room temperature fracture compressive strain (increased to 5000 με), tensile strength (increased to 140 MPa), flexural strength (increased to 200 MPa), and 0.2 MPa compression set (compression set decreased to 0.5%). The typical ballistic heating environment heat resistance temperature has increased from 1000℃ to 1500℃.

[0052] Example 3

[0053] This embodiment provides a preparation process for a lightweight integrated heat-insulating ceramic composite material. First, a ceramic composite preform is designed. The ceramic composite preform has a sandwich structure, including a core layer, an upper surface layer, and a lower surface layer. The core layer, upper surface layer, and lower surface layer are connected by silica fiber bundle puncture lines. The core layer is silica fiber felt, and the upper and lower surface layers are silica fiber cloth. The thickness of the core layer is 25 mm; the thickness of the upper surface layer is 4.0 mm; and the thickness of the lower surface layer is 1 mm. The ceramic composite preform is prepared by supercritical drying (refer to the methods disclosed in Chinese Patents 200510031952.0, 200710034510.0, 201110110844.8, 201110110947.4, 201110110946.X, 201010300112.0, or 201010148105.3); the treated ceramic composite preform is then subjected to… The preform was subjected to hydrophobic treatment by immersion in a tetraethyl orthosilicate solution at atmospheric pressure for 90 minutes at 60°C. The preform was then clamped in a mold and immersed in a modified silica sol, followed by curing. This process was repeated three times, with the curing temperature at 200°C. Under vacuum conditions, the preform was subjected to pyrolysis sintering and cooled to room temperature at 900°C for 20 minutes to obtain a lightweight, heat-insulating integrated ceramic composite material.

[0054] The basic properties of the lightweight integrated heat-resistant and heat-insulating ceramic composite material in Example 3 are as follows:

[0055] (1) The thickness of the lightweight heat-resistant and heat-insulating integrated ceramic composite material is 25mm and the density is 0.59g / cm3;

[0056] (2) The room temperature fracture compressive strain of the lightweight heat-resistant and heat-insulating integrated ceramic composite material is 5000με, the tensile strength is 140MPa, and the flexural strength is 180MPa.

[0057] (3) The room temperature thickness direction compression deformation of the lightweight heat-insulating integrated ceramic composite material is 0.4% at 0.2 MPa.

[0058] (4) The lightweight heat-resistant and heat-insulating integrated ceramic composite material prepared in this embodiment was subjected to a quartz lamp single-sided radiation heating test at 1500℃ for 1 hour. After the test, the surface structure of the lightweight heat-resistant and heat-insulating integrated ceramic composite material was intact and there was no obvious damage, indicating that the material system can be used normally at 1500℃ for a long time, and the back temperature was 540℃.

[0059] Compared to the high-temperature resistant, heat-insulating sandwich-structure ceramic matrix composite material obtained after implementation of CN112094130A, the preparation method of the lightweight heat-insulating integrated ceramic composite material provided in this embodiment has a shorter preparation cycle (only 3 impregnation and curing cycles). The material exhibits significant performance improvements in room temperature fracture compressive strain (increased to 5000 με), tensile strength (increased to 140 MPa), flexural strength (increased to 180 MPa), and 0.2 MPa compression set (compression set decreased to 0.4%). The typical ballistic heating environment heat resistance temperature is increased to 1500℃.

[0060] As can be seen from the examples, the lightweight heat-resistant and heat-insulating integrated ceramic composite material of the present invention has a high heat resistance temperature and significantly shortens the material preparation cycle from the initial 8-12 times to 3-5 times. This effectively shortens the preparation cycle, improves the preparation efficiency, and is simple to operate. It has broad prospects for large-scale production of ceramic matrix composite materials in the industrial field.

[0061] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for preparing a lightweight, heat-resistant, and heat-insulating integrated ceramic composite material, characterized in that, Includes the following steps: S1. Design the core layer thickness, upper surface layer thickness, and lower surface layer thickness, as well as the material system. The upper surface layer thickness is greater than the lower surface layer thickness. The core layer is a silica fiber cotton felt, and the upper and lower surface layers are both silica fiber cloth. S2. Based on the design in step S1, prepare the ceramic composite material preform; S3. Preparation of aerogel composite materials: Supercritical drying is used to prepare ceramic composite preforms. S4. The ceramic composite preform treated in S3 is subjected to hydrophobic treatment. The ceramic composite preform is immersed in tetraethyl orthosilicate solution and then subjected to high temperature treatment. S5. Clamp the ceramic composite preform processed in step S4 with a mold, immerse it in the modified silica sol, and then cure it. Repeat the immersion and curing process 3 to 5 times. S6. Under vacuum conditions, the preform treated in step S5 is subjected to pyrolysis sintering and cooled to room temperature to obtain a lightweight heat-resistant and heat-insulating integrated ceramic composite material, wherein the core layer thickness of the composite material is 20-300 mm; and / or The thickness of the upper surface layer is 2.0~5.0 mm; and / or The thickness of the lower surface layer is 0.3~1.0 mm; The core layer is an aerogel composite material with a porous ceramic structure; the upper surface layer is an oxide fiber ceramic matrix composite material, serving as the hot surface; and the lower surface layer is an oxide fiber ceramic matrix composite material, serving as the cold surface.

2. The method for preparing the lightweight heat-resistant and heat-insulating integrated ceramic composite material according to claim 1, characterized in that, The hydrophobication treatment in step S4 is carried out at a temperature of 30~100℃ for 30~120 min.

3. The preparation method of the lightweight heat-resistant and heat-insulating integrated ceramic composite material according to claim 1, characterized in that, In step S5, the impregnation is performed under normal pressure at a temperature of 50~200℃.

4. The method for preparing the lightweight heat-resistant and heat-insulating integrated ceramic composite material according to claim 3, characterized in that, In step S5, the curing temperature is 100~400℃.

5. The method for preparing the lightweight heat-resistant and heat-insulating integrated ceramic composite material according to claim 4, characterized in that, In step S6, the pyrolysis firing temperature is 700~1200℃ and the time is 10~40min.

6. A lightweight, heat-resistant, and heat-insulating integrated ceramic composite material, characterized in that, The lightweight heat-resistant and heat-insulating integrated ceramic composite material is prepared by any one of claims 1 to 5.

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