CN-122011942-A - Heat-proof and oxidation-resistant coating and preparation and application thereof

Abstract

The invention relates to the technical field of aerospace thermal protection materials, in particular to an anti-heat insulation and oxidation resistance coating, and preparation and application thereof. The heat-proof and oxidation-resistant coating comprises the following components in percentage by mass, wherein the sum of the mass percentages of the components is 100%, the solid content of the heat-proof and oxidation-resistant coating is more than or equal to 55%, the heat-proof and oxidation-resistant coating is a mixture of HfSiO 4 、CaSiO 3 , silicon powder and SiB 6 , the high-emissivity filler is a mixture of an atomic-level complex-phase high-entropy oxide coating material, tiB 2 , tungsten carbide, tantalum carbide and chromium carbide, the film-forming agent is a mixture of an organosilicon modified polyester resin intermediate HY-3074, polysilazane and zinc sulfate, the auxiliary is a composition of white carbon black and KH570, and the solvent is one or more of isopropanol, butanol or ethyl acetate, and the coating can be further applied to the field of spacecraft protection.

Inventors

• GUO FANGWEI
• HE LING
• XU JIALI
• CUI YUNLONG
• HUANG QIANJUN

Assignees

• 上海交通大学

Dates

Publication Date

20260512

Application Date

20260212

Claims (10)

1. 1. The heat-proof and oxidation-resistant coating is characterized by comprising the following components in percentage by mass: 45-70 wt% of variable-temperature porcelain agent, 6.5-20 wt% of high-emissivity filler, 5-10 wt% of film forming agent, 0.5-1.5 wt% of auxiliary agent and other solvents; Wherein the sum of the mass percentages of the components is 100%, and the solid content of the heat-proof and oxidation-resistant coating is more than or equal to 55%; the temperature-changing porcelain agent is a mixture of HfSiO 4 、CaSiO 3 , silicon powder and SiB 6 ; The high emissivity filler is a mixture of an atomic-level complex-phase high-entropy oxide coating material, tiB 2 , tungsten carbide, tantalum carbide and chromium carbide; the film forming agent is a mixture of an organosilicon modified polyester resin intermediate HY-3074, polysilazane and zinc sulfate; the auxiliary agent is a composition of white carbon black and KH 570; The solvent is one or more of isopropanol, butanol or ethyl acetate.
2. 2. The heat-proof and oxidation-resistant coating according to claim 1, wherein the mass ratio of HfSiO 4 、CaSiO 3 to silicon powder to SiB 6 is 15-35:15-35:5-15.
3. 3. The heat-proof and oxidation-resistant coating according to claim 1, wherein the mass ratio of the atomic-level complex-phase high-entropy oxide coating material to the TiB 2 to the tungsten carbide to the tantalum carbide to the chromium carbide is 55-85:5-10:2-5:2-8:2-5.
4. 4. The heat-proof and oxidation-resistant coating according to claim 1, wherein the mass ratio of the organosilicon modified polyester resin intermediate HY-3074 to polysilazane to zinc sulfate is 4-5:5-10:1-2.
5. 5. The heat-proof and oxidation-resistant coating according to claim 1, wherein the mass part ratio of white carbon black to KH570 is 1.25-3.0:0.25-1.25.
6. 6. A method for preparing the heat-proof, heat-insulating and oxidation-resistant coating according to any one of claims 1 to 5, comprising the following steps: (S1) mixing a variable-temperature porcelain agent, a high-emissivity filler, a film forming agent, a part of auxiliary agent and a solvent, and performing ball milling treatment to obtain a suspension coating; and (S2) transferring the suspension coating obtained in the step (S1) into a degassing tank, and adding the residual auxiliary agent to eliminate bubbles to obtain the heat-proof and oxidation-resistant coating.
7. 7. An application of the heat-proof, heat-insulating and oxidation-resistant coating in the field of spacecraft protection.
8. 8. A method of using the heat-insulating oxidation-resistant coating according to any one of claims 1 to 5, comprising the steps of: (A1) Carrying out sand blasting treatment and/or cleaning treatment on the base material, and drying to obtain a pretreated base material; (A2) And uniformly spraying the heat-proof and oxidation-resistant coating on the surface of the pretreated substrate by using compressed air spraying equipment, and curing after the spraying is finished to form a coating on the surface of the substrate.
9. 9. The method of claim 8, wherein in the step (A2), the temperature is room temperature, the spraying thickness is 25 μm per pass, and the target coating thickness is 100-300 μm.
10. 10. The method for using an anti-heat and oxidation-resistant coating according to claim 8, wherein in the step (A2), the temperature is room temperature and the time is 24-48 h in the curing process.

Description

Heat-proof and oxidation-resistant coating and preparation and application thereof Technical Field The invention relates to the technical field of aerospace thermal protection materials, in particular to an anti-heat insulation and oxidation resistance coating, and preparation and application thereof. Background When the repeatable carrier rocket reenters the atmosphere, the parts such as the head part, the front edge of the wing and the like can face the extreme aerodynamic heating environment, and the surface temperature can reach more than 1600 ℃ and even locally reach 2000 ℃. This puts extremely severe demands on the thermal protection system, which must have excellent high temperature resistance, ablation resistance, heat insulation, and scouring resistance, and also must have good thermal shock resistance, high emissivity to radiate heat, and long-term weather resistance. The ceramic fiber rigid heat-proof tile has high porosity and low volume weight, has stable shape and certain strength at high temperature, has excellent functions of radiation heat dissipation, heat insulation, scouring resistance and pneumatic appearance maintenance, and becomes one of the most main materials for large-area heat protection of the surface of the current aerospace craft. In order to avoid the damage of the heat-proof tile caused by the scouring of high-speed air flow and reduce the heat quantity transferred into the tile, a compact coating which has good oxidation resistance and high radiation coefficient and can keep good thermal shock resistance in a large temperature change range is generally coated on the surface of the heat-proof tile. The coating with high emissivity can radiate heat into the surrounding environment, and consume a large amount of pneumatic heat, so that the heat transmitted into the heat-proof tile is reduced efficiently, and the ideal heat-proof effect is achieved. The main components of the coating material are 3% -5% of B 2O3、75%~90% SiO2, 1% -5% of a radiation agent (SiB 4、MoSi2 and TaSi 2) and the like, the coating is sprayed on the surface of the fiber heat-proof tile through an atmospheric spraying technology, and the final composite coating heat-proof tile is manufactured by firing in an air atmosphere with the temperature of more than 1200 ℃ after drying. During the preparation process and the flight service process, after the borosilicate glass component in the coating is subjected to thermal exposure, the radiation agent powder undergoes thermal oxidation reaction, so that micropores are formed on the surface of the coating, the number of the micropores increases along with the increase of the number of thermal exposure, and the anti-scouring capability of the coating is reduced to fall off in a large area and even be damaged. Therefore, for on-orbit or ground maintenance, developing an anti-heat insulation tile surface high-emissivity oxidation-resistant coating material capable of being quickly sprayed and repaired at room temperature and a simple construction process matched with the anti-heat insulation tile surface high-emissivity oxidation-resistant coating material are important for prolonging the service life of a carrier rocket and reducing the maintenance cost. Disclosure of Invention In order to solve the problems, the invention aims to provide an anti-heat insulation and oxidation-resistant coating, and preparation and application thereof, wherein the coating has excellent comprehensive performance and is suitable for room-temperature construction and repair. The heat-insulating tile has the characteristics of low damage rate at ultrahigh temperature, excellent heat-insulating performance, high emissivity, firm combination, water repellency, moisture resistance and the like, and is particularly suitable for heat protection and repair of the surfaces of aluminum, magnesium, titanium alloy and ceramic-based heat-insulating tiles. The aim of the invention can be achieved by the following technical scheme: The invention provides an anti-heat insulation and oxidation-resistant coating, which comprises the following components in percentage by mass: a variable temperature vitrification agent, a high emissivity filler, a film forming agent, an auxiliary agent and a solvent; Wherein the sum of the mass percentages of the components is 100 percent, and the solid content of the heat-proof and oxidation-resistant coating is more than or equal to 55 percent (so as to ensure that a coating with enough thickness can be obtained by one-time spraying); The variable-temperature porcelain agent is a mixture of HfSiO 4、CaSiO3, silicon powder and SiB 6, and can provide ceramic film forming performance for the inner coating at 80-1800 ℃, so that the ultrahigh-temperature resistance of the coating is effectively improved, and the ceramic-formed coating has good thermal stability and thermal shock resistance; The high-emissivity filler is a mixture of an atomic-level complex-phase high-entropy