Space high-stability high-reflection radiation heat dissipation coating, coating and preparation method thereof

Abstract

The invention provides a spatial high-stability and high-reflection radiation heat dissipation coating, a coating and a preparation method of the coating. The heat dissipation coating comprises a prime coating and a surface coating, the prime paint comprises the following components in percentage by volume: 50-60% of zinc orthotitanate; 1.5%-4.5% of indium tin oxide; 35.5%-48.5% of a potassium silicate aqueous solution; the surface layer coating comprises the following components in percentage by volume: 30-35% of gallium oxide; 30%-35% of barium sulfate; the volume fraction is determined according to the condition that the solid content of the potassium silicate aqueous solution is 30wt%. According to the spatial high-stability and high-reflection radiation heat dissipation coating, the coating and the preparation method thereof, through the component design of the bottom layer and the surface layer, the scattering capacity to different spectral energy of sunlight and the tolerance to vacuum ionization irradiation are greatly improved, and the design requirements of high precision and long service life of modern novel spacecrafts can be met.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft thermal control coatings, and in particular relates to a space high-stability and high-reflection radiation heat dissipation paint, coating and a preparation method thereof. Background Art

[0002] Thermal control coating is an important thermal management functional material in spacecraft. It is widely used in products such as thermal radiators, structural panels, electronic units, antennas, electric propulsion, and sunshades. It is the most widely used thermal control material in spacecraft. Its function is to use the coating to change the surface thermophysical properties of the object and maintain the balance of energy absorption and radiation on the inner and outer surfaces, so as to effectively control the temperature of the object during the radiation heat exchange process, so that the operating temperature of the internal instruments and equipment of the spacecraft does not exceed the allowable range during the heat exchange process between the inside and outside. For components, the failure rate increases by an order of magnitude for every 25°C increase (reliability decreases by 10% for every 2°C increase). Almost all visible inner and outer surfaces of spacecraft are thermal control coatings. Among them, the spray-type low-absorption and high-emission thermal control coating is the most used, widely used, and most significant type of thermal control coating in spacecraft due to its advantages such as simple construction, wide product adaptability, and low cost. During the satellite's in-orbit operation, it will face the harsh space environment. Therefore, the thermal control coating is required to have excellent thermal physical properties and excellent space environment stability to ensure that the temperature control meets the requirements of each unit and payload during the satellite's life cycle.

[0003] Most of the existing low-absorption and high-emission thermal control coatings are traditional ZnO filler systems. In the past 50 years, they have played an important role in low-orbit spacecraft thermal control coating products due to their excellent shielding performance in the ultraviolet band of 200nm to 380nm. However, their high solar absorption (≥0.15) and sensitivity to ionizing radiation optical defects (reflectivity drops to below 40% at the end of their life) limit their use in the harsh radiation environments of medium and high orbits, and cannot meet the higher performance requirements of my country's subsequent missions. Summary of the invention

[0004] In order to overcome the deficiencies in the prior art, the inventors have conducted intensive research and provided a space high-stability and high-reflection radiation heat dissipation paint, coating and preparation method thereof. Through the design of the base and surface layer components, the scattering ability of different spectral energies of sunlight and the tolerance to vacuum ionizing radiation are greatly increased, so that it can meet the high-precision and long-life design requirements of modern new spacecraft.

[0005] The technical solution provided by the present invention is as follows:

[0006] In the first aspect, a spatially highly stable and highly reflective radiation heat dissipation coating comprises a base coating and a surface coating;

[0007] The primer, based on a solid content of 30 wt% of the potassium silicate aqueous solution, comprises the following components in volume fractions:

[0008] Zinc titanate 50% to 60%;

[0009] Indium tin oxide 1.5% to 4.5%;

[0010] Potassium silicate aqueous solution 35.5%~48.5%;

[0011] The surface coating, based on the solid content of the potassium silicate aqueous solution being 30wt%, comprises the following components in volume fractions:

[0012] Gallium oxide 30% to 35%;

[0013] Barium sulfate 30%-35%;

[0014] Potassium silicate aqueous solution 30% to 40%.

[0015] In a second aspect, a spatially highly stable and highly reflective radiation heat dissipation coating comprises a primer layer and a top coating layer, and is prepared using the spatially highly stable and highly reflective radiation heat dissipation coating described in the first aspect.

[0016] In a third aspect, a method for preparing a spatially highly stable and highly reflective radiation heat dissipation coating comprises:

[0017] The zinc titanate, indium tin oxide and potassium silicate aqueous solution are mixed, ground and dispersed to disperse and mix the primer, and after the grinding and dispersion is completed, the grinding medium is removed by filtering to obtain the primer;

[0018] Gallium oxide, barium sulfate and potassium silicate aqueous solutions are mixed, ground and dispersed to disperse and mix the surface coating. After the grinding and dispersion is completed, the grinding medium is filtered to remove the grinding medium to obtain the surface coating.

[0019] In a fourth aspect, a method for preparing a space high-stability and high-reflection radiation heat dissipation coating comprises:

[0020] First, a primer is sprayed on the surface of the substrate with a primer, and then a topcoat is sprayed with a topcoat. The thickness of each spraying is controlled at 15μm to 20μm. The next spraying is carried out after the surface is dry. After spraying, it is cured at room temperature, baked at 50-60℃ for 4h to 6h, and baked at 80-90℃ for 24h to 36h. After baking, it is naturally cooled to room temperature to obtain a spatially highly stable and highly reflective radiation heat dissipation coating.

[0021] A spatially highly stable and highly reflective radiation heat dissipation coating, coating and preparation method thereof provided by the present invention has the following beneficial effects:

[0022] (1) The present invention provides a space high-stability and high-reflection radiation heat dissipation coating, coating and preparation method thereof. Zinc titanate (Zn2TiO4) powder with high reflectivity in the visible light and near-infrared bands is selected in the bottom filler, and the optimal spectral reflection particle size distribution range is determined; indium tin oxide (ITO) with different graded particle sizes is selected as an anti-static filler. By matching different particle sizes, a conductive path is constructed inside the coating while ensuring the overall reflective performance of the coating. Gallium oxide (GaO2) and barium sulfate (BaSO4) fillers resistant to vacuum ionizing radiation are selected as surface layer fillers. The particle size range of GaO2 is controlled to ensure the ultraviolet band reflective performance of the surface layer, and BaSO4 fillers with finer particle sizes are selected to improve the emissivity of the surface layer. The overall coating has excellent solar spectrum reflective performance and infrared emission performance, and can have less degradation of solar absorption ratio after large doses of electron radiation. It is suitable for most commonly used substrates for spacecraft and plays an important role in the long-term stability of the thermal control performance of long-life spacecraft on orbit;

[0023] (2) The present invention provides a highly stable and highly reflective radiation heat dissipation coating having the following characteristics:

[0024] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0025] 2) Solar absorption ratio: 0.07~0.09;

[0026] 3) Hemispherical emissivity: 0.90-0.92;

[0027] 4) Volume resistivity: ρ V =1×10 5 Ω·m~1×10 7 Ω·m.

[0028] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating.

[0029] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm2 After series irradiation, the change in solar absorption ratio is ≤0.20, the change in hemispherical emissivity is ≤0.02, and the thermal cycle performance meets the requirements. DETAILED DESCRIPTION

[0030] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0031] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0032] The present invention provides a spatially highly stable and highly reflective radiation heat dissipation coating, comprising a base coating and a surface coating;

[0033] The primer, based on a solid content of 30 wt% of the potassium silicate aqueous solution, comprises the following components in volume fractions:

[0034] Zinc titanate (Zn2TiO4) 50% to 60%;

[0035] Indium tin oxide (ITO) 1.5% to 4.5%;

[0036] Potassium silicate aqueous solution 35.5%~48.5%;

[0037] The surface coating, based on the solid content of the potassium silicate aqueous solution being 30wt%, comprises the following components in volume fractions:

[0038] Gallium oxide (GaO2) 30% to 35%;

[0039] Barium sulfate (BaSO4) 30% to 35%;

[0040] Potassium silicate aqueous solution 30% to 40%;

[0041] The above volume fraction is determined based on the solid content of the potassium silicate aqueous solution being 30 wt %, that is, the above volume fraction varies according to the solid content of the potassium silicate aqueous solution.

[0042] Zinc titanate (Zn2TiO4) and indium tin oxide (ITO) are selected as coating fillers in the bottom coating, the median particle size D50 of Zn2TiO4 is 1.2μm-1.6μm, and the purity is ≥99.9wt%; the median particle size D50 of ITO is 50nm-100nm, 0.5μm-0.7μm, 1.2μm-1.6μm, and there are three levels, and the purity is ≥99.9wt%, wherein the volume fraction of 50nm-100nm ITO in the bottom coating is 0.5%-1.5%, the volume fraction of 0.5μm-0.7μm ITO in the bottom coating is 0.5%-1.5%, and the volume fraction of 1.2μm-1.6μm ITO in the bottom coating is 0.5%-1.5%. Potassium silicate aqueous solution is selected as coating binder in the bottom coating.

[0043] Gallium oxide (GaO2) and barium sulfate (BaSO4) are selected as coating fillers in the surface coating, the median particle size D50 of GaO2 is 3μm-5μm, the purity is ≥99.9wt%, and the median particle size D50 of BaSO4 is 0.5μm-0.8μm, the purity is ≥99.9wt%. Potassium silicate aqueous solution is selected as coating binder in the surface coating.

[0044] Correspondingly, the present invention also provides a spatial high-stability and high-reflection radiation heat dissipation coating, which is prepared using the above-mentioned spatial high-stability and high-reflection radiation heat dissipation coating; the thickness of the base coating is 100μm to 120μm, and the thickness of the top coating is 10 to 30μm.

[0045] The present invention also provides a method for preparing a spatially highly stable and highly reflective radiation heat dissipation coating, comprising the following steps:

[0046] (1) Preparation of primer: Zn2TiO4, ITO and potassium silicate aqueous solution are mixed. If the concentration of the potassium silicate aqueous solution is too high, deionized water is added to dilute it so that the solid content of the potassium silicate aqueous solution is 7wt% to 15wt%. The primer is dispersed and mixed by grinding and dispersion. The grinding medium is zirconium oxide, which is spherical, has a purity of ≥99.9wt%, and a particle size of 5mm to 10mm. The volume of the grinding medium is 70% to 85%, the rotation speed is 150 to 250rpm, and the grinding and dispersion time is 3h to 6h. After the grinding and dispersion is completed, the slurry is taken out and filtered with a 80-200 mesh gauze to obtain the primer.

[0047] (2) Preparation of surface coating: Mix GaO2, BaSO4 and potassium silicate aqueous solution. If the concentration of the potassium silicate aqueous solution is too high, add deionized water to dilute it so that the solid content of the potassium silicate aqueous solution is 7wt% to 15wt%. Grinding and dispersing are used to disperse and mix the surface coating. The grinding medium is zirconium oxide, which is spherical, has a purity of ≥99.9wt%, and a particle size of 5mm to 10mm. The volume of the grinding medium is 70% to 85%, the rotation speed is 150 to 250rpm, and the grinding and dispersing time is 3h to 6h. After the grinding and dispersing is completed, the slurry is taken out and filtered with a 80-200 mesh gauze to obtain the surface coating.

[0048] The prepared base coating and surface coating are used to prepare a space high-stability and high-reflection radiation heat dissipation coating, including:

[0049] (3) Before spraying the substrate, clean the surface with aviation gasoline, acetone and ethanol, and then perform pre-treatment by grinding or sandblasting before spraying the coating; first spray the base coating with a base coating, and then spray the top coating with a top coating. The thickness of each spraying is controlled at 15μm to 20μm. After the surface is dry, the next spraying is performed. After spraying, it is cured at room temperature for 12h to 24h, baked at 45 to 55℃ for 4h to 6h, and baked at 80 to 100℃ for 24h to 36h. After baking, it is naturally cooled to room temperature to obtain a high-stability, high-reflection radiation heat dissipation coating.

[0050] Example

[0051] Example 1

[0052] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0053] Composition of base coating : The volume fraction of Zn2TiO4 (D50=1.2μm) in the primer is 50%. The volume fraction of ITO (D50=50nm) in the primer is 0.5%, the volume fraction of ITO (D50=0.5μm) in the primer is 0.5%, the volume fraction of ITO (D50=1.2μm) in the primer is 0.5%, and the volume fraction of potassium silicate aqueous solution (solid content is 30wt%) in the primer is 48.5%.

[0054] Composition of surface coating : The volume fraction of GaO2 (D50 = 3 μm) in the surface coating is 30%, the volume fraction of BaSO4 (D50 = 0.5 μm) in the surface coating is 30%. The volume fraction of potassium silicate aqueous solution (solid content of 30wt%) in the surface coating is 40%. The thickness of the primer is 100 μm, and the thickness of the top coating is 10 μm.

[0055] (1) Preparation of base coating: Zn2TiO4, ITO and potassium silicate aqueous solution are mixed, and deionized water is added. The mass ratio of potassium silicate aqueous solution to deionized water is 1:2.4. Grinding and dispersion are used to disperse and mix the base coating. The grinding medium is zirconium oxide. The zirconium oxide is spherical, has a purity of ≥99.9%, and a particle size of 5mm. The grinding medium volume is 70%, the rotation speed is 150rpm, and the grinding and dispersion time is 3h. After the grinding and dispersion is completed, the slurry is taken out and filtered through an 80-mesh gauze to obtain the base coating.

[0056] (2) Preparation of surface coating: Mix GaO2, BaSO4 and potassium silicate aqueous solution, add deionized water, the mass ratio of potassium silicate aqueous solution to deionized water is 1:2.4. Grinding and dispersion are used to disperse and mix the base coating, the grinding medium is zirconium oxide, the zirconium oxide is spherical, the zirconium oxide purity is ≥99.9%, the zirconium oxide particle size is 5mm, the grinding medium volume is 70%, the rotation speed is 150rpm, and the grinding and dispersion time is 3h. After the grinding and dispersion is completed, the slurry is taken out and filtered with an 80-mesh gauze to obtain the surface coating.

[0057] (3) Preparation of high-stable and high-reflective radiation heat dissipation coating for space: Before spraying the substrate, aviation gasoline, acetone and ethanol are used to clean the surface, and the coating is sprayed after grinding or sandblasting. The primer is sprayed first and then the topcoat is sprayed. The thickness of each spraying is controlled at 15 μm. After the surface is dry, the next spraying is carried out. After spraying, it is cured at room temperature for 12 hours, baked at 50°C for 4 hours, and baked at 80°C for 24 hours. After baking, it is naturally cooled to room temperature to obtain a high-stable and high-reflective radiation heat dissipation coating for space.

[0058] The spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0059] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0060] 2) Solar absorption ratio: 0.09;

[0061] 3) Hemispheric emissivity: 0.92;

[0062] 4) Volume resistivity: ρ V =5.3×10 6 Ω·m;

[0063] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0064] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change of solar absorption ratio is 0.20, the change of hemispherical emissivity is 0.02, and the thermal cycle performance meets the requirements.

[0065] Example 2

[0066] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0067] Composition of base coating : The volume fraction of Zn2TiO4 (D50=1.6μm) in the primer is 60%. The volume fraction of ITO (D50=100nm) in the primer is 1.5%, the volume fraction of ITO (D50=0.7μm) in the primer is 1.5%, the volume fraction of ITO (D50=1.6μm) in the primer is 1.5%, and the volume fraction of potassium silicate aqueous solution (solid content is 30wt%) in the primer is 35.5%.

[0068] Composition of surface coating : The volume fraction of GaO2 (D50 = 5 μm) in the topcoat is 35%, the volume fraction of BaSO4 (D50 = 0.8 μm) in the topcoat is 35%. The volume fraction of potassium silicate aqueous solution (solid content of 30 wt%) in the topcoat is 30%. The thickness of the basecoat is 120 μm, and the thickness of the topcoat is 30 μm.

[0069] (1) Preparation of base coating: Zn2TiO4, ITO and potassium silicate aqueous solution are mixed, and deionized water is added. The mass ratio of potassium silicate aqueous solution to deionized water is 1:3.2. Grinding and dispersion are used to disperse and mix the base coating. The grinding medium is zirconium oxide. The zirconium oxide is spherical, has a purity of ≥99.9%, and a particle size of 10 mm. The grinding medium volume is 85%, the rotation speed is 250 rpm, and the grinding and dispersion time is 6 hours. After the grinding and dispersion is completed, the slurry is taken out and filtered with a 200-mesh gauze to obtain the base coating.

[0070] (2) Preparation of surface coating: Mix GaO2, BaSO4 and potassium silicate aqueous solution, add deionized water, the mass ratio of potassium silicate aqueous solution to deionized water is 1:3.2. Grinding and dispersion are used to disperse and mix the base coating, the grinding medium is zirconium oxide, the zirconium oxide is spherical, the purity is ≥99.9%, the particle size is 10mm, the grinding medium volume is 85%, the rotation speed is 250rpm, and the grinding and dispersion time is 6h. After the grinding and dispersion is completed, the slurry is taken out and filtered with a 200-mesh gauze to obtain the surface coating.

[0071] (3) Preparation of high-stable and high-reflective radiation heat dissipation coating for space: Before spraying the substrate, aviation gasoline, acetone and ethanol are used to clean the surface, and the coating is sprayed after grinding or sandblasting. The primer is sprayed first and then the topcoat is sprayed. The thickness of each spraying is controlled at 20 μm. After the surface is dry, the next spraying is carried out. After spraying, it is cured at room temperature for 24 hours, baked at 50°C for 6 hours, and baked at 80°C for 36 hours. After baking, it is naturally cooled to room temperature to obtain a high-stable and high-reflective radiation heat dissipation coating for space.

[0072] The spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0073] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0074] 2) Solar absorption ratio: 0.08;

[0075] 3) Hemispheric emissivity: 0.92;

[0076] 4) Volume resistivity: ρ V =2.1×10 5 Ω·m;

[0077] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0078] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2After series irradiation, the change of solar absorption ratio is 0.18, the change of hemispherical emissivity is 0.01, and the thermal cycle performance meets the requirements.

[0079] Example 3

[0080] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0081] Composition of base coating : The volume fraction of Zn2TiO4 (D50=1.4μm) in the primer is 55%. The volume fraction of ITO (D50=80nm) in the primer is 1.0%, the volume fraction of ITO (D50=0.6μm) in the primer is 1.0%, the volume fraction of ITO (D50=1.4μm) in the primer is 1.0%, and the volume fraction of potassium silicate aqueous solution (solid content is 30wt%) in the primer is 42%.

[0082] Composition of surface coating : The volume fraction of GaO2 (D50 = 4 μm) in the topcoat is 35%, the volume fraction of BaSO4 (D50 = 0.6 μm) in the topcoat is 30%. The volume fraction of potassium silicate aqueous solution (solid content of 30 wt%) in the topcoat is 35%. The thickness of the basecoat is 110 μm, and the thickness of the topcoat is 20 μm.

[0083] (1) Preparation of base coating: First, Zn2TiO4, ITO and potassium silicate aqueous solution are mixed, and deionized water is added. The mass ratio of potassium silicate aqueous solution to deionized water is 1:2.8. Grinding and dispersion are used to disperse and mix the base coating. The grinding medium is zirconium oxide. The zirconium oxide is spherical, has a purity of ≥99.9%, and a particle size of 8mm. The grinding medium volume is 80%, the rotation speed is 200rpm, and the grinding and dispersion time is 4h. After the grinding and dispersion is completed, the slurry is taken out and filtered through a 150-mesh gauze to obtain the base coating.

[0084] (2) Preparation of surface coating: Mix GaO2, BaSO4 and potassium silicate aqueous solution, add deionized water, the mass ratio of potassium silicate aqueous solution to deionized water is 1:2.8. Grinding and dispersion are used to disperse and mix the base coating, the grinding medium is zirconium oxide, the zirconium oxide is spherical, the purity is ≥99.9%, the particle size is 8mm, the grinding medium volume is 80%, the rotation speed is 200rpm, and the grinding and dispersion time is 4h. After the grinding and dispersion is completed, the slurry is taken out and filtered with a 120-mesh gauze to obtain the surface coating.

[0085] (3) Preparation of high-stable and high-reflective radiation heat dissipation coating for space: Before spraying the substrate, aviation gasoline, acetone and ethanol are used to clean the surface, and the coating is sprayed after grinding or sandblasting. The primer is sprayed first and then the topcoat is sprayed. The thickness of each spraying is controlled at 20 μm. After the surface is dry, the next spraying is carried out. After spraying, it is cured at room temperature for 16 hours, baked at 50°C for 6 hours, and baked at 80°C for 36 hours. After baking, it is naturally cooled to room temperature to obtain a high-stable and high-reflective radiation heat dissipation coating for space.

[0086] The spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0087] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0088] 2) Solar absorption ratio: 0.07;

[0089] 3) Hemispheric emissivity: 0.92;

[0090] 4) Volume resistivity: ρ V =4.7×10 5 Ω·m;

[0091] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0092] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change of solar absorption ratio is 0.19, the change of hemispherical emissivity is 0.01, and the thermal cycle performance meets the requirements.

[0093] Example 4

[0094] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0095] Composition of base coatingThe volume fraction of Zn2TiO4 (D50=1.2μm) in the primer is 50%, the volume fraction of ITO (D50=0.5μm) in the primer is 1.5%, and the volume fraction of potassium silicate aqueous solution (solid content is 30wt%) in the primer is 48.5%.

[0096] Composition of surface coating : Same as Example 1.

[0097] The preparation method of the radiation heat dissipation coating is the same as that of Example 1, which will not be described in detail here. A spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0098] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0099] 2) Solar absorption ratio: 0.07;

[0100] 3) Hemispheric emissivity: 0.92;

[0101] 4) Volume resistivity: ρ V =2.3×10 7 Ω·m;

[0102] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0103] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change in solar absorption ratio is 0.21, and the change in hemispherical emissivity is 0.02.

[0104] Example 5

[0105] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0106] Composition of base coating: The volume fraction of Zn2TiO4 (D50=0.8μm) in the primer is 50%. The volume fraction of ITO (D50=50nm) in the primer is 0.5%, the volume fraction of ITO (D50=0.5μm) in the primer is 0.5%, the volume fraction of ITO (D50=1.2μm) in the primer is 0.5%, and the volume fraction of potassium silicate aqueous solution (solid content is 30wt%) in the primer is 48.5%.

[0107] Composition of surface coating : Same as Example 1.

[0108] The preparation method of the heat dissipation coating is the same as that of Example 1, and will not be described in detail here. A spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0109] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0110] 2) Solar absorption ratio: 0.12;

[0111] 3) Hemispheric emissivity: 0.90;

[0112] 4) Volume resistivity: ρ V =5.7×10 6 Ω·m;

[0113] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0114] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change in solar absorption ratio is 0.24, and the change in hemispherical emissivity is 0.02.

[0115] Example 6

[0116] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0117] Composition of base coating : The volume fraction of Zn2TiO4 (D50=2.5μm) in the primer is 50%. The volume fraction of ITO (D50=50nm) in the primer is 0.5%, the volume fraction of ITO (D50=0.5μm) in the primer is 0.5%, the volume fraction of ITO (D50=1.2μm) in the primer is 0.5%, and the volume fraction of potassium silicate aqueous solution (solid content is 30wt%) in the primer is 48.5%.

[0118] Composition of surface coating : Same as Example 1.

[0119] The preparation method of the heat dissipation coating is the same as that of Example 1, and will not be described in detail here. A spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0120] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0121] 2) Solar absorption ratio: 0.13;

[0122] 3) Hemispheric emissivity: 0.88;

[0123] 4) Volume resistivity: ρ V =8.6×10 6 Ω·m;

[0124] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0125] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change in solar absorption ratio is 0.25, and the change in hemispherical emissivity is 0.02.

[0126] Example 7

[0127] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0128] Composition of base coating : Same as Example 1.

[0129] Composition of surface coating : The volume fraction of GaO2 (D50 = 1.5 μm) in the surface coating is 30%, the volume fraction of BaSO4 (D50 = 0.5 μm) in the surface coating is 30%. The volume fraction of potassium silicate aqueous solution (solid content of 30wt%) in the surface coating is 40%. The thickness of the primer is 100 μm, and the thickness of the top coating is 10 μm.

[0130] The preparation method of the heat dissipation coating is the same as that of Example 1, and will not be described in detail here. A spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0131] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0132] 2) Solar absorption ratio: 0.12;

[0133] 3) Hemispheric emissivity: 0.91;

[0134] 4) Volume resistivity: ρ V =6.4×10 6 Ω·m;

[0135] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0136] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change in solar absorption ratio is 0.23, and the change in hemispherical emissivity is 0.02.

[0137] Example 8

[0138] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0139] Composition of base coating : Same as Example 1.

[0140] Composition of surface coating : The volume fraction of GaO2 (D50 = 7.5 μm) in the surface coating is 30%, the volume fraction of BaSO4 (D50 = 0.5 μm) in the surface coating is 30%. The volume fraction of potassium silicate aqueous solution (solid content of 30wt%) in the surface coating is 40%. The thickness of the primer is 100 μm, and the thickness of the top coating is 10 μm.

[0141] The preparation method of the heat dissipation coating is the same as that of Example 1, and will not be described in detail here. A spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0142] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0143] 2) Solar absorption ratio: 0.13;

[0144] 3) Hemispheric emissivity: 0.90;

[0145] 4) Volume resistivity: ρ V =7.5×10 6 Ω·m;

[0146] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0147] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2After series irradiation, the change in solar absorption ratio is 0.24, and the change in hemispherical emissivity is 0.02.

[0148] Example 9

[0149] A space high-stability and high-reflection radiation heat dissipation paint and coating, the composition and preparation method of which are as follows:

[0150] Composition of base coating : Same as Example 1.

[0151] Composition of surface coating : The volume fraction of GaO2 (D50 = 3 μm) in the surface coating is 30%, the volume fraction of BaSO4 (D50 = 2 μm) in the surface coating is 30%. The volume fraction of potassium silicate aqueous solution (solid content of 30wt%) in the surface coating is 40%. The thickness of the primer is 100 μm, and the thickness of the top coating is 10 μm.

[0152] The preparation method of the heat dissipation coating is the same as that of Example 1, and will not be described in detail here. A spatially highly stable and highly reflective radiation heat dissipation coating of the present invention has the following characteristics:

[0153] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0154] 2) Solar absorption ratio: 0.13;

[0155] 3) Hemispheric emissivity: 0.91;

[0156] 4) Volume resistivity: ρ V =6.8×10 6 Ω·m;

[0157] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0158] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2After series irradiation, the change in solar absorption ratio is 0.22, and the change in hemispherical emissivity is 0.02.

[0159] Comparative Example

[0160] Comparative Example 1

[0161] The comparative example 1 is consistent with the example 1, except that ZnO with a median particle size of 1.2 μm is used in the primer instead of Zn2TiO4, and the volume fraction of ZnO in the primer is 50%.

[0162] The prepared coating has the following characteristics:

[0163] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0164] 2) Solar absorption ratio: 0.20;

[0165] 3) Hemispheric emissivity: 0.92;

[0166] 4) Volume resistivity: ρ V =2.5×10 7 Ω·m;

[0167] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0168] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change in solar absorption ratio is 0.30, and the change in hemispherical emissivity is 0.03.

[0169] Comparative Example 2

[0170] This comparative example 2 is consistent with example 1, and the only difference is that the surface coating does not contain GaO2.

[0171] The prepared coating has the following characteristics:

[0172] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0173] 2) Solar absorption ratio: 0.18;

[0174] 3) Hemispheric emissivity: 0.90;

[0175] 4) Volume resistivity: ρ V =1.2×10 7 Ω·m;

[0176] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0177] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change in solar absorption ratio is 0.26, and the change in hemispherical emissivity is 0.02.

[0178] Comparative Example 3

[0179] This comparative example 3 is consistent with example 1, and the only difference is that the top coating does not contain BaSO4.

[0180] The prepared coating has the following characteristics:

[0181] 1) Appearance: The coating is uniformly white, without bubbles, peeling, cracking, falling off, etc.

[0182] 2) Solar absorption ratio: 0.16;

[0183] 3) Hemispheric emissivity: 0.91;

[0184] 4) Volume resistivity: ρ V =8.3×10 6 Ω·m;

[0185] 5) Thermal cycle performance: The surface coating of aluminum alloy, titanium alloy, magnesium alloy, stainless steel, pure iron, ablative material, carbon fiber composite material and other substrates shall be subjected to 100 times of thermal cycle test at -196℃~+200℃ according to the standard, and there shall be no bubbles, peeling, cracking, falling off and other phenomena on the coating;

[0186] 6) Radiation resistance: After no less than 5000ESH vacuum-ultraviolet irradiation, the irradiation energy is 15keV and the total injection is 3.2×10 16 e / cm 2 The irradiation energy is 30 keV and the total injection is 2.0×10 16 e / cm 2 The irradiation energy is 60 keV and the total injection is 0.5×10 16 e / cm 2 The vacuum electron irradiation was carried out with an irradiation energy of 50 keV and a total injection of 2.0×10 16 p / cm 2 After series irradiation, the change in solar absorption ratio is 0.25, and the change in hemispherical emissivity is 0.02.

[0187] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0188] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A spatially highly stable and highly reflective radiation heat dissipation coating, characterized in that: Including primer and topcoat; The primer, based on a solid content of 30 wt% of the potassium silicate aqueous solution, comprises the following components in volume fractions: Zinc titanate 50% to 60%; Indium tin oxide 1.5% to 4.5%; Potassium silicate aqueous solution 35.5%~48.5%; The surface coating, based on the solid content of the potassium silicate aqueous solution being 30wt%, comprises the following components in volume fractions: Gallium oxide 30% to 35%; Barium sulfate 30%-35%; Potassium silicate aqueous solution 30% to 40%.

2. The spatially highly stable and highly reflective radiation heat dissipation coating according to claim 1, characterized in that: The median particle size of the zinc titanate is 1.2 μm to 1.6 μm.

3. The spatially highly stable and highly reflective radiation heat dissipation coating according to claim 1, characterized in that: The median particle size of the indium tin oxide is 50nm-100nm, 0.5μm-0.7μm, and 1.2μm-1.6μm, with a total of three grades, wherein the volume fraction of the indium tin oxide of 50nm-100nm in the primer is 0.5%-1.5%, the volume fraction of the indium tin oxide of 0.5μm-0.7μm in the primer is 0.5%-1.5%, and the volume fraction of the indium tin oxide of 1.2μm-1.6μm in the primer is 0.5%-1.5%.

4. The spatially highly stable and highly reflective radiation heat dissipation coating according to claim 1, characterized in that: The median particle size of the gallium oxide is 3 μm to 5 μm.

5. The spatially highly stable and highly reflective radiation heat dissipation coating according to claim 1, characterized in that: The median particle size of the barium sulfate is 0.5 μm to 0.8 μm.

6. A spatially highly stable and highly reflective radiation heat dissipation coating, characterized in that: The invention comprises a primer layer and a top coat layer, and is prepared by using the spatially highly stable and highly reflective radiation heat dissipation coating material as claimed in any one of claims 1 to 5.

7. The spatial high-stability and high-reflection radiation heat dissipation coating according to claim 6, characterized in that: The thickness of the primer layer is 100 μm to 120 μm, and the thickness of the top layer is 10 to 30 μm.

8. A method for preparing the spatially highly stable and highly reflective radiation heat dissipation coating according to any one of claims 1 to 5, characterized in that: include: The zinc titanate, indium tin oxide and potassium silicate aqueous solution are mixed, ground and dispersed to disperse and mix the primer, and after the grinding and dispersion is completed, the grinding medium is removed by filtering to obtain the primer; Gallium oxide, barium sulfate and potassium silicate aqueous solutions are mixed, ground and dispersed to disperse and mix the surface coating. After the grinding and dispersion is completed, the grinding medium is filtered to remove the grinding medium to obtain the surface coating.

9. The method for preparing the spatially highly stable and highly reflective radiation heat dissipation coating according to claim 8, characterized in that: When preparing the primer, when the solid content of the potassium silicate aqueous solution is greater than 15wt%, it is diluted with deionized water to make the solid content of the potassium silicate aqueous solution 7wt% to 15wt%; When preparing the surface coating, when the solid content of the potassium silicate aqueous solution used is greater than 15wt%, it is diluted with deionized water to make the solid content of the potassium silicate aqueous solution 7wt% to 15wt%.

10. A method for preparing a spatial high-stability and high-reflection radiation heat dissipation coating according to claim 6 or 7, characterized in that: include: First, a primer is sprayed on the surface of the substrate with a primer, and then a topcoat is sprayed with a topcoat. The thickness of each spraying is controlled at 15μm to 20μm. The next spraying is carried out after the surface is dry. After spraying, it is cured at room temperature, baked at 45-55℃ for 4h to 6h, and baked at 80-100℃ for 24h to 36h. After baking, it is naturally cooled to room temperature to obtain a spatially highly stable and highly reflective radiation heat dissipation coating.