Heat-proof and heat-insulation oxidation-resistant coating as well as preparation and application thereof

Abstract

The invention relates to the technical field of aerospace thermal protection materials, in particular to a heat-proof and heat-insulation oxidation-resistant coating as well as preparation and application thereof. The heat-proof and heat-insulation oxidation-resistant coating is prepared from the following components in percentage by mass: a variable-temperature porcelainizing agent, a high-emissivity filler, a film-forming agent, an auxiliary agent and a solvent, wherein the sum of the mass percentages of all the components is 100%, and the solid content of the heat-proof and heat-insulation oxidation-resistant coating is larger than or equal to 55%. The variable temperature porcelainizing agent is a mixture of HfSiO4, CaSiO3, silicon powder and SiB6; the high-emissivity filler is a mixture of an atomic-scale complex-phase high-entropy oxide coating material, TiB2, tungsten carbide, tantalum carbide and chromium carbide; the film-forming agent is a mixture of an organic silicon modified polyester resin intermediate HY-3074, polysilazane and zinc sulfate; the auxiliary agent is a composition of white carbon black and KH570; the solvent is one or more of isopropanol, butanol or ethyl acetate; the coating can be further applied to the field of spacecraft protection.

Description

Technical Field

[0001] This invention relates to the field of aerospace thermal protection materials technology, and in particular to a heat-insulating and oxidation-resistant coating and its preparation and application. Background Technology

[0002] When reusable launch vehicles re-enter the atmosphere, their nose cones, wing leading edges, and other parts face extreme aerodynamic heating environments, with surface temperatures reaching over 1600°C, and even locally exceeding 2000°C. This places extremely stringent requirements on thermal protection systems: they must possess excellent high-temperature resistance, ablation resistance, heat insulation, and erosion resistance, while also exhibiting good thermal shock resistance, high emissivity for radiative heat dissipation, and long-term weather resistance. Ceramic fiber rigid thermal insulation tiles have high porosity and low density, maintaining a stable shape and certain strength at high temperatures. They also provide excellent radiative heat dissipation, heat insulation, erosion resistance, and maintain aerodynamic shape, making them one of the most important materials for large-area thermal protection on the surface of spacecraft. To prevent the thermal insulation tiles from being damaged by high-speed airflow and to reduce the heat transferred into the tiles, a dense coating with good oxidation resistance, a high emissivity, and good thermal shock resistance over a wide temperature range is typically applied to their surface. A coating with a high emissivity can dissipate heat into the surrounding environment through radiation, consuming a large amount of aerodynamic heat, thus efficiently reducing the heat transferred into the heat-insulating tile and achieving an ideal heat-insulating effect. The main components of the coating material are 3%~5% B2O3, 75%~90% SiO2, and 1%~5% radiation agents (SiB4, MoSi2, and TaSi2), etc. The coating is sprayed onto the surface of the fiber heat-insulating tile using atmospheric spraying technology, and after drying, it is fired in an air atmosphere at a high temperature of over 1200 ℃ to form the final composite coating heat-insulating tile. During the manufacturing process and flight service, the borosilicate glass component in the coating undergoes a thermal oxidation reaction after heat exposure, resulting in the formation of micropores on the coating surface. The number of micropores increases with the number of heat exposures, leading to a decrease in the coating's erosion resistance and large-area peeling or even damage.

[0003] Therefore, for on-orbit or ground maintenance, developing a high-emissivity, oxidation-resistant coating material for heat-insulating tiles that can be rapidly sprayed and repaired at room temperature, along with a simple construction process, is crucial for extending the lifespan of launch vehicles and reducing maintenance costs. Summary of the Invention

[0004] To address the aforementioned problems, the present invention aims to provide a heat-resistant and oxidation-resistant coating, its preparation, and its application. This coating exhibits excellent overall performance and is suitable for room-temperature application and repair. It features low damage rate at ultra-high temperatures, excellent heat-resistant and insulating properties, high emissivity, strong adhesion, and hydrophobic and moisture-proof characteristics, making it particularly suitable for thermal protection and repair of aluminum, magnesium, titanium alloys, and ceramic-based heat-resistant and insulating tile surfaces.

[0005] The objective of this invention can be achieved through the following technical solutions: The first objective of this invention is to provide a heat-insulating and oxidation-resistant coating, comprising the following components in weight percentages: Temperature-changing ceramicizing agent, high emissivity filler, film-forming agent, additives and solvents; The total mass percentage of each component is 100%, and the solid content of the heat-insulating and oxidation-resistant coating is ≥55% (to ensure that a sufficiently thick coating can be obtained in one spray). The temperature-varying ceramicizing agent is a mixture of HfSiO4, CaSiO3, silicon powder and SiB6. The temperature-varying ceramicizing agent can provide ceramic film formation performance of the coating within 80~1800 ℃, thereby effectively improving the coating's resistance to ultra-high temperature. After the coating is ceramicized, it has good thermal stability and thermal shock resistance. The high emissivity filler is a mixture of atomic-level multiphase high-entropy oxide coating material, TiB2, tungsten carbide, tantalum carbide and chromium carbide. The high emissivity filler is designed to significantly improve the radiation heat dissipation capacity of the coating at high temperatures, so that the emissivity of the coating remains above 0.92 for a long time at high temperatures. The film-forming agent is a mixture of silicone-modified polyester resin intermediate HY-3074, polysilazane, and zinc sulfate (ZnSO4); it is used to formulate ceramic powder into a coating at room temperature, which can be sprayed onto the substrate surface at room temperature to form a film. ZnSO4 can be used in the range of 280~600 ℃ to improve the flame retardant and smoke suppression properties of the coating, and polysilazane can be converted into ceramic in subsequent use to enhance the bonding force of the ceramic components inside the coating.

[0006] The additive is a composition of silica and KH570, used to maintain uniform mixing of the coating and remove air bubbles; The solvent is one or more of isopropanol, butanol, or ethyl acetate, used to adjust the viscosity of the heat-insulating and oxidation-resistant coating to suit the spraying operation.

[0007] In one embodiment of the present invention, the mass ratio of HfSiO4, CaSiO3, silicon powder and SiB6 is 15~35:15~35:15~35:5~15.

[0008] In one embodiment of the present invention, the mass ratio of atomic-level multiphase high-entropy oxide coating material, TiB2, tungsten carbide (WC), tantalum carbide (TaC) and chromium carbide (Cr2C3) is 55~85:5~10:2~5:2~8:2~5; The atomic-level multiphase high-entropy oxide coating material is the atomic-level multiphase high-entropy oxide coating material of patent CN120717814A.

[0009] In one embodiment of the present invention, the mass ratio of organosilicon-modified polyester resin intermediate HY-3074, polysilazane, and zinc sulfate is 4~5:5~10:1~2.

[0010] In one embodiment of the present invention, the mass ratio of silica to KH570 is 1.25~3.0:0.25~1.25.

[0011] The second objective of this invention is to provide a method for preparing a heat-insulating and oxidation-resistant coating, comprising the following steps: (S1) After mixing the temperature-varying ceramicizing agent, high emissivity filler, film-forming agent, some additives and solvent, the mixture is ball-milled (to ensure that each component is fully dispersed in the solvent) to obtain a suspension coating. (S2) Transfer the suspended coating obtained in step (S1) into a degassing tank, add the remaining additives to eliminate bubbles, and obtain a heat-insulating and oxidation-resistant coating.

[0012] The third objective of this invention is to provide an application of a heat-insulating and oxidation-resistant coating in the field of spacecraft protection.

[0013] The fourth objective of this invention is to provide a method for using a heat-insulating and oxidation-resistant coating, comprising the following steps: (A1) The substrate is sandblasted and / or cleaned (to remove oxide layer and dirt), and then dried to obtain the pretreated substrate; (A2) Use compressed air spraying equipment to evenly spray the heat-insulating and oxidation-resistant coating onto the pretreated substrate surface. After spraying, perform curing treatment to form a coating on the substrate surface.

[0014] In one embodiment of the present invention, in step (A1), the substrate includes, but is not limited to, aluminum, magnesium, titanium alloy or ceramic-based heat-insulating tiles.

[0015] In one embodiment of the present invention, in step (A2), during the spraying process, the temperature is room temperature, the spraying pressure is 0.2~0.45 MPa, the spraying distance is 20~50 cm, the spraying thickness is 25 μm per pass, and the target coating thickness is 100~350 μm.

[0016] In one embodiment of the present invention, in step (A2), the curing process is carried out at room temperature for 24 to 48 hours (no additional heating treatment is required).

[0017] Compared with the prior art, the present invention has the following beneficial effects: (1) Excellent resistance to ultra-high temperature: The coating has a quality damage rate of less than 2% in a high temperature environment of 1600~2000 ℃, and can effectively resist ultra-high temperature ablation and oxidation.

[0018] (2) High radiation heat dissipation capacity: The emissivity of the coating surface is higher than 0.92, which can efficiently dissipate heat through radiation.

[0019] (3) Strong bonding and durability: The coating is tightly bonded to the substrate interface, without cracking, with good thermal shock resistance and resistance to aerodynamic erosion.

[0020] (4) Good environmental adaptability: The coating surface is hydrophobic, moisture-proof, salt spray resistant, and has high weather resistance, making it suitable for long-term storage and use in various environments.

[0021] (5) Wide range of substrate applicability: This coating can be applied to aluminum, magnesium and titanium alloy surfaces, as well as to the sealing and reinforcement of ceramic-based heat-insulating tile surfaces.

[0022] (6) Convenient construction: It adopts room temperature compressed air spraying technology, which does not require complicated equipment and high temperature sintering process. It is especially suitable for rapid on-site construction and repair of large structural components, and has low maintenance cost.

[0023] (7) The coating of the present invention can also reduce the solvent content (below 15%) and be formulated into a high viscosity paste for use in repairing cracks in heat-insulating tiles, heat-insulating sealing and bonding. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the macroscopic morphology of the coating after it has been sprayed and dried on the titanium alloy surface in Example 2; Figure 2 The image shows the surface morphology of the coating on the titanium alloy surface in Example 2 after being tested at a high temperature of 1700 °C (15 min). Figure 3 The image shows the surface XRD phase diagram of the coating on the titanium alloy surface in Example 2 after being tested at a high temperature of 1700 °C (15 min). Figure 4 The image shows the cross-sectional morphology of the interface between the coating on the titanium alloy surface and the Ti substrate after the coating has been tested at a high temperature of 1700℃ (15 min) in Example 2. Figure 5 (a) is a macroscopic morphology of the ceramic-based heat-insulating tile surface after the first coating is applied and dried in Example 3, and (b) is a morphology of the ceramic-based heat-insulating tile surface after five thermal cycles and the coating is reapplied and repaired. Figure 6 The macroscopic morphology of the sample after the anti-heat insulation and oxidation resistant coating was sprayed and dried on the surface of ceramic fiber aerogel anti-heat insulation tile in Example 3, after ablation thermal cycling treatment and after recoating and repair: (a) 1250 ℃-5 min for one ablation thermal cycle, (b) 1250 ℃-5 min for five ablation thermal cycles. Figure 7SEM micrographs of the initial, ablation, and repair states of the ceramic fiber aerogel heat-insulating tile surface after spraying with heat-insulating and oxidation-resistant coating in Example 3: (a) Initial sample coating surface, (b) Coating surface after five ablation thermal cycles of 1250 ℃-5 min, (c) Ablation coating surface after grinding and spraying repair. Detailed Implementation

[0025] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0026] In the following embodiments, the atomic-level multiphase high-entropy oxide coating material is the atomic-level multiphase high-entropy oxide coating material prepared in Example 1 of patent CN120717814A; unless otherwise specified, all reagents used are commercially available reagents, and all detection methods and techniques used are conventional detection methods and techniques in the field.

[0027] Example 1 This embodiment provides a method for preparing a heat-insulating and oxidation-resistant coating, wherein the heat-insulating and oxidation-resistant coating is composed of the following components by mass percentage: Temperature-changing ceramicizing agent, high emissivity filler, film-forming agent, additives and solvents; The temperature-changing ceramicizing agent is a mixture of HfSiO4 (15 wt%), CaSiO3 (35 wt%), silicon powder (15 wt%) and SiB6 (5 wt%). The high emissivity filler is a mixture of atomic-level multiphase high-entropy oxide coating material (5 wt%), TiB2 (0.5 wt%), tungsten carbide (0.25 wt%), tantalum carbide (0.25 wt%), and chromium carbide (0.25 wt%). The film-forming agent is a mixture of silicone-modified polyester resin intermediate HY-3074 (4 wt%), polysilazane (5 wt%), and zinc sulfate (1 wt%). The additive is a composition of silica (1.25 wt%) and KH570 (0.25 wt%). The solvent is ethyl acetate (balance).

[0028] Includes the following steps: (S1) After mixing the temperature-varying ceramicizing agent, high emissivity filler, film-forming agent, some additives (0.5 wt% of additives are reserved for later use) and solvent, the mixture is ball-milled for 6 hours to obtain a suspension coating. (S2) Transfer the suspended coating into a degassing tank and add the remaining 0.5 wt% of additives to eliminate bubbles, thus obtaining a heat-insulating and oxidation-resistant coating.

[0029] Example 2 This embodiment provides a method for using a heat-insulating and oxidation-resistant coating, including the following steps: (A1) The titanium alloy sheet is sandblasted, then cleaned with ethanol and dried to obtain a pretreated titanium alloy sheet. (A2) Using a common compressed air spray gun, the heat-insulating and oxidation-resistant coating prepared in Example 1 was sprayed onto the surface of the pretreated titanium alloy plate obtained in step (A1) at 25 ℃. The wet film thickness of the sprayed coating was controlled to be 350 μm (spraying pressure was 0.3 MPa, spraying distance was 35 cm, and spraying thickness was 25 μm per pass). (A3) After step (A2) is completed, allow it to stand at room temperature for 24 hours to complete curing, forming a coating on the surface of the titanium alloy sheet (see schematic diagram of macroscopic morphology). Figure 1 (As shown).

[0030] Performance Analysis: A schematic diagram of the macroscopic morphology of the coating on the surface of the titanium alloy sheet is shown below. Figure 1 As shown in the figure, the surface morphology SEM image of the coating on the titanium alloy sheet after high temperature testing at 1700 ℃ (15 min) is as follows. Figure 2 As shown, the XRD pattern is as follows Figure 3 As shown, the cross-sectional morphology of the interface between the coating and the Ti substrate is as follows. Figure 4 As shown; pass Figure 1 and Figure 2 The coating morphology on the surface of the titanium alloy sheet before and after heat treatment shows that the coating surface is uniform and free from ablation defects such as cracks, bubbles, sagging, and peeling. This indicates that the coating has good thermal compatibility with the metal substrate after being ceramicized by heat. This provides key excellent stress-strain matching performance of the coating interface for long-term heat insulation and oxidation resistance of titanium alloy hot-end components of various high-performance aerospace vehicles.

[0031] pass Figures 2-4 It can be observed that the coating has a mass loss of 1.5% under the oxyacetylene flame test at 1700 ℃; the surface emissivity at room temperature is 0.92; and the cross-sectional SEM shows that the coating is dense and crack-free, and has good adhesion to the substrate.

[0032] Example 3 This embodiment provides a method for using a heat-insulating and oxidation-resistant coating, including the following steps: (A1) The ceramic-based heat-insulating tile is sandblasted, then cleaned with ethanol and dried to obtain the pretreated ceramic-based heat-insulating tile. (A2) Using a common compressed air spray gun, the heat-insulating and oxidation-resistant coating prepared in Example 1 was sprayed onto the pretreated ceramic-based heat-insulating tile surface obtained in step (A1) at 25 ℃. The wet film thickness of the sprayed coating was controlled to be 300 μm (spraying pressure was 0.3 MPa, spraying distance was 35 cm, and spraying thickness was 25 μm per pass). (A3) After step (A2) is completed, let it stand at room temperature for 24 hours to complete the curing and form a coating on the surface of the ceramic-based heat-insulating tile.

[0033] Performance Analysis: Figure 5 (a) is a macroscopic morphology image of the ceramic fiber aerogel heat-insulating tile surface after the first coating is applied and dried in this embodiment; (b) is a morphology image of the ceramic fiber aerogel heat-insulating tile surface after recoating and repairing with coating after five thermal cycles (1250 ℃ - 5 min). Figure 5 It can be observed that the obtained coating can effectively penetrate into the pores of the ceramic fiber aerogel heat insulation tile, playing a good sealing and reinforcing role. After high temperature testing, its performance is comparable to that of Example 1.

[0034] Figure 6 Macroscopic morphology images of the coating prepared in Example 1 after spraying and drying on the surface of ceramic fiber aerogel heat-insulating tile, after ablation thermal cycling treatment and after recoating and repair: (a) 1250 ℃-5 min for one ablation thermal cycle, (b) 1250 ℃-5 min for five ablation thermal cycles; Figure 7 SEM micrographs of the initial, ablation, and repaired states of the ceramic fiber aerogel heat-insulating tile after spraying coating: (a) initial sample coating surface, (b) coating surface after five ablation thermal cycles of 1250 ℃-5 min, (c) ablation coating surface after grinding and spraying repair. Figure 6 and Figure 7 It can be observed that the coating has excellent room temperature spray curing and molding capabilities, and its surface structure is stable under high temperature flame ablation thermal cycling simulation conditions, resisting thermal shock and exhibiting near-zero ablation shape retention.

[0035] Example 4 This embodiment provides a method for preparing a heat-insulating and oxidation-resistant coating, wherein the heat-insulating and oxidation-resistant coating is composed of the following components by mass percentage: Temperature-changing ceramicizing agent, high emissivity filler, film-forming agent, additives and solvents; The temperature-changing ceramicizing agent is a mixture of HfSiO4 (13 wt%), CaSiO3 (37 wt%), silicon powder (13 wt%) and SiB6 (7 wt%); The high emissivity filler is a mixture of atomic-level multiphase high-entropy oxide coating material (5 wt%), TiB2 (0.5 wt%), tungsten carbide (0.25 wt%), tantalum carbide (0.25 wt%), and chromium carbide (0.25 wt%). The film-forming agent is a mixture of silicone-modified polyester resin intermediate HY-3074 (6 wt%), polysilazane (5 wt%), and zinc sulfate (2 wt%). The additive is a composition of silica (1.5 wt%) and KH570 (0.5 wt%); The solvent is ethyl acetate (balance).

[0036] Includes the following steps: (S1) After mixing the temperature-varying ceramicizing agent, high emissivity filler, film-forming agent, some additives (0.5 wt% of additives are reserved for later use) and solvent, the mixture is ball-milled for 6 hours to obtain a suspension coating. (S2) Transfer the suspended coating into a degassing tank and add the remaining 0.5 wt% of additives to eliminate bubbles, thus obtaining a heat-insulating and oxidation-resistant coating.

[0037] Example 5 This embodiment provides a method for preparing a heat-insulating and oxidation-resistant coating, wherein the heat-insulating and oxidation-resistant coating is composed of the following components by mass percentage: Temperature-changing ceramicizing agent, high emissivity filler, film-forming agent, additives and solvents; The temperature-changing ceramicizing agent is a mixture of HfSiO4 (17 wt%), CaSiO3 (33 wt%), silicon powder (16 wt%) and SiB6 (4 wt%); The high emissivity filler is a mixture of atomic-level multiphase high-entropy oxide coating material (5 wt%), TiB2 (0.5 wt%), tungsten carbide (0.25 wt%), tantalum carbide (0.25 wt%), and chromium carbide (0.25 wt%). The film-forming agent is a mixture of silicone-modified polyester resin intermediate HY-3074 (4 wt%), polysilazane (5 wt%), and zinc sulfate (2 wt%). The additive is a composition of silica (3 wt%) and KH570 (0.5 wt%). The solvent is isopropanol (balance).

[0038] Includes the following steps: (S1) After mixing the temperature-varying ceramicizing agent, high emissivity filler, film-forming agent, some additives (0.5 wt% of additives are reserved for later use) and solvent, the mixture is ball-milled for 6 hours to obtain a suspension coating. (S2) Transfer the suspended coating into a degassing tank and add the remaining 0.5 wt% of additives to eliminate bubbles, thus obtaining a heat-insulating and oxidation-resistant coating.

[0039] Example 6 This embodiment provides a method for preparing a heat-insulating and oxidation-resistant coating, wherein the heat-insulating and oxidation-resistant coating is composed of the following components by mass percentage: Temperature-changing ceramicizing agent, high emissivity filler, film-forming agent, additives and solvents; The temperature-changing ceramicizing agent is a mixture of HfSiO4 (15 wt%), CaSiO3 (35 wt%), silicon powder (15 wt%) and SiB6 (5 wt%). The high emissivity filler is a mixture of atomic-level multiphase high-entropy oxide coating material (5 wt%), TiB2 (0.5 wt%), tungsten carbide (0.25 wt%), tantalum carbide (0.25 wt%), and chromium carbide (0.25 wt%). The film-forming agent is a mixture of silicone-modified polyester resin intermediate HY-3074 (4 wt%), polysilazane (5 wt%), and zinc sulfate (1 wt%). The additive is a composition of silica (1.25 wt%) and KH570 (0.25 wt%). The solvent is butanol (balance).

[0040] Includes the following steps: (S1) After mixing the temperature-varying ceramicizing agent, high emissivity filler, film-forming agent, some additives (0.5 wt% of additives are reserved for later use) and solvent, the mixture is ball-milled for 6 hours to obtain a suspension coating. (S2) Transfer the suspended coating into a degassing tank and add the remaining 0.5 wt% of additives to eliminate bubbles, thus obtaining a heat-insulating and oxidation-resistant coating.

[0041] The heat-insulating and oxidation-resistant coatings prepared in Examples 4 to 6 have basically the same performance as the heat-insulating and oxidation-resistant coating prepared in Example 1.

[0042] In summary, this invention provides a high-performance thermal protection coating and method with comprehensive performance and convenient construction, which has broad application prospects in the field of high-temperature and ultra-high-temperature surface protection for reusable launch vehicles and hypersonic vehicles.

[0043] The above description of the embodiments is provided to enable those skilled in the art to understand and use the invention. It will be apparent to those skilled in the art that various modifications can be made to these embodiments, and the general principles described herein can be applied to other embodiments without inventive effort. Therefore, the present invention is not limited to the above embodiments, and any improvements and modifications made by those skilled in the art based on the interpretation of the present invention, without departing from the scope of the invention, should be within the protection scope of the present invention.

Claims

1. A heat-insulating and oxidation-resistant coating, characterized in that, It consists of the following components by mass percentage: 45~70 wt% temperature-varying ceramicizing agent, 6.5~20 wt% high emissivity filler, 5~10 wt% film-forming agent, 0.5~1.5 wt% additives and other solvents; The total mass percentage of each component is 100%, and the solid content of the heat-insulating and oxidation-resistant coating is ≥55%. The temperature-changing ceramicizing agent is a mixture of HfSiO4, CaSiO3, silicon powder and SiB6; The high emissivity filler is a mixture of atomically multiphase high-entropy oxide coating material, TiB2, tungsten carbide, tantalum carbide and chromium carbide; The film-forming agent is a mixture of organosilicon-modified polyester resin intermediate HY-3074, polysilazane, and zinc sulfate; The additive is a combination of silica and KH570; The solvent is one or more of isopropanol, butanol, or ethyl acetate.

2. The heat-insulating and oxidation-resistant coating according to claim 1, characterized in that, The mass ratio of HfSiO4, CaSiO3, silicon powder and SiB6 is 15~35:15~35:15~35:5~15.

3. The heat-insulating and oxidation-resistant coating according to claim 1, characterized in that, The mass ratio of atomic-level multiphase high-entropy oxide coating material, TiB2, tungsten carbide, tantalum carbide and chromium carbide is 55~85:5~10:2~5:2~8:2~5.

4. The heat-insulating and oxidation-resistant coating according to claim 1, characterized in that, The mass ratio of organosilicon-modified polyester resin intermediate HY-3074, polysilazane, and zinc sulfate is 4~5:5~10:1~2.

5. The heat-insulating and oxidation-resistant coating according to claim 1, characterized in that, The mass ratio of silica to KH570 is 1.25~3.0:0.25~1.

25.

6. A method for preparing a heat-insulating and oxidation-resistant coating as described in any one of claims 1 to 5, characterized in that, Includes the following steps: (S1) After mixing the temperature-varying ceramicizing agent, high emissivity filler, film-forming agent, some additives and solvent, the mixture is ball-milled to obtain a suspension coating. (S2) Transfer the suspended coating obtained in step (S1) into a degassing tank, add the remaining additives to eliminate bubbles, and obtain a heat-insulating and oxidation-resistant coating.

7. The application of the heat-insulating and oxidation-resistant coating as described in any one of claims 1 to 5 in the field of spacecraft protection.

8. A method of using the heat-insulating and oxidation-resistant coating as described in any one of claims 1 to 5, characterized in that, Includes the following steps: (A1) The substrate is sandblasted and / or cleaned, and then dried to obtain the pretreated substrate; (A2) Use compressed air spraying equipment to evenly spray the heat-insulating and oxidation-resistant coating onto the pretreated substrate surface. After spraying, perform curing treatment to form a coating on the substrate surface.

9. The method of using the heat-insulating and oxidation-resistant coating according to claim 8, characterized in that, In step (A2), the temperature is room temperature during the spraying process, the spraying thickness is 25 μm per pass, and the target coating thickness is 100~300 μm.

10. The method of using the heat-insulating and oxidation-resistant coating according to claim 8, characterized in that, In step (A2), the curing process is carried out at room temperature for 24 to 48 hours.

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