CN109337575B - Preparation method of satellite outer surface heat-insulating coating - Google Patents
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Abstract
A preparation method of a satellite outer surface heat insulation coating comprises the following raw materials: polysiloxane, tetraethoxysilane, rutile titanium dioxide, xylene, sulfuric acid, polyurethane acrylate, polyether, 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, alkyl phosphate diethanolamine salt, cuprous oxide, chromium oxide, ethyl acetate, cobalt naphthenate solution, aluminum powder, graphene dispersion liquid, zircon powder and aluminum hydroxide, and the mixture is uniformly mixed and ground to obtain the catalyst; the storage period is 1-2 years, the solid content is 70-80%, and the high temperature of 250-; all the components have a synergistic effect, the acid resistance is good, the 10 percent nitric acid is not foamed or dropped after 7-9d, the radiation coefficient En is more than or equal to 0.85, the wear resistance is excellent, and the flexibility is 1-3 mm; the paint has the advantages of aviation lubricant resistance for 4-8 months, good conductivity, excellent heat-insulating property and plump and bright paint film; has excellent electric performance and aviation endurance.
Description
Technical Field
The invention relates to a thermal insulation coating, in particular to a preparation method of a thermal insulation coating on the outer surface of a satellite.
Background
The heat insulation coating is a coating which is coated on the surface to be constructed and can play a role in heat insulation, is called a heat insulation coating, and is divided into a transparent heat insulation coating and a non-transparent heat insulation coating according to different use occasions; according to the heat insulation mechanism, the heat insulation coating can be divided into 3 types of barrier heat insulation coating, reflective heat insulation coating and radiation heat insulation coating.
Aiming at the climatic characteristics of different areas, a scheme of combining external wall external heat preservation is provided, various heat insulation coatings are reasonably selected and used, a comfortable indoor heat environment is generated, and the purpose of saving energy is achieved.
Building energy conservation is one of the key points of energy-saving work in China, and external wall external heat preservation becomes a main product of building energy conservation. For areas mainly used for heat preservation in thermal engineering design, such as severe cold areas and cold areas, external wall external heat preservation is reasonable, applicable and fast in development. For the hot and warm areas in summer, which are generally only considered for heat insulation during thermal design, or the hot and cold areas in summer, which are mainly used for heat insulation during thermal design, a further perfect space exists for the external heat insulation of some external walls at present. The method is characterized in that various heat-insulating coatings are reasonably selected and used according to a solar radiation heat balance equation of a building enclosure structure and the climatic characteristics of different regions to form a composite system, so that heat is insulated, and the purposes of comfortable indoor thermal environment, energy conservation and consumption reduction are achieved.
The coating is mainly prepared from nano hollow microspheres, high-grade emulsion, titanium dioxide and the like, wherein the content of the nano hollow microspheres in the coating is at least more than 80%, the coating can form a three-dimensional network hollow structure connected by closed microspheres on the surface of an object after being coated, a static air group which is sandwiched in a stacking manner is formed between the nano hollow ceramic microspheres and the microspheres, namely heat insulation units, the heat conductivity coefficient of the coating can reach 0.04W/m.K, the heat conduction can be effectively prevented, the heat insulation and heat preservation are excellent, the heat insulation grade of the coating reaches R-30.1, the heat reflectivity is more than 90%, a large amount of infrared rays can be reflected, the object is prevented from being heated by the infrared rays, the radiation heat and the heat conduction of the sun and the infrared rays can be effectively inhibited, and the heat insulation and heat preservation inhibition efficiency can reach about 90%.
Disclosure of Invention
The invention provides a preparation method of a satellite outer surface heat insulation coating, which solves the technical problems that the existing satellite outer surface heat insulation coating is not high temperature resistant, low in radiation coefficient, poor in flexibility, not corrosion resistant and the like.
The invention adopts the following technical scheme: a preparation method of a satellite outer surface heat insulation coating comprises the following steps:
the first step is as follows: weighing 100 parts of polysiloxane, 50-70 parts of tetraethoxysilane, 1-5 parts of rutile titanium dioxide, 4-8 parts of xylene, 10-20 parts of sulfuric acid, 40-60 parts of polyurethane acrylate, 1-5 parts of polyether, 15-35 parts of 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, 8-16 parts of alkyl phosphate diethanol amine salt, 11-15 parts of cuprous oxide, 4-8 parts of chromium oxide, 10-20 parts of ethyl acetate, 3-7 parts of cobalt naphthenate liquid, 10-30 parts of aluminum powder, 10-30 parts of graphene dispersion liquid, 2-7 parts of zircon powder and 1-3 parts of aluminum hydroxide according to the mass part ratio of the components;
the second step is that: putting polysiloxane, tetraethoxysilane, rutile titanium dioxide, xylene and sulfuric acid into a reaction kettle with a thermometer, a heating device and a stirring device, stirring for 30-50min at 30-40 ℃, stirring at 80-100 r/min, heating to 50-60 ℃, adding urethane acrylate, polyether, 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, alkyl phosphate diethanol amine salt, cuprous oxide and chromium oxide, and continuously stirring for 30-40min at 90-110 r/min;
the third step: heating to 60-70 ℃, adding ethyl acetate, cobalt naphthenate solution, aluminum powder and graphene dispersion, stirring for 40-50min at the stirring speed of 100-;
the fourth step: and after being uniformly ground, the mixture is constructed by a spraying method, dried for 10-30min after being sprayed, and then cured into a film at the temperature of 200-220 ℃.
As a preferred technical scheme of the invention: the raw materials comprise the following components in parts by weight: 100 parts of polysiloxane, 50 parts of tetraethoxysilane, 1 part of rutile titanium dioxide, 4 parts of dimethylbenzene, 10 parts of sulfuric acid, 40 parts of polyurethane acrylate, 1 part of polyether, 15 parts of 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, 8 parts of alkyl phosphate diethanol amine salt, 11 parts of cuprous oxide, 4 parts of chromium oxide, 10 parts of ethyl acetate, 3 parts of cobalt naphthenate solution, 10 parts of aluminum powder, 10 parts of graphene dispersion solution, 2 parts of zircon powder and 1 part of aluminum hydroxide.
As a preferred technical scheme of the invention: the raw materials comprise the following components in parts by weight: 100 parts of polysiloxane, 70 parts of tetraethoxysilane, 5 parts of rutile titanium dioxide, 8 parts of xylene, 20 parts of sulfuric acid, 60 parts of polyurethane acrylate, 5 parts of polyether, 35 parts of 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, 16 parts of alkyl phosphate diethanol amine salt, 15 parts of cuprous oxide, 8 parts of chromium oxide, 20 parts of ethyl acetate, 7 parts of cobalt naphthenate solution, 30 parts of aluminum powder, 30 parts of graphene dispersion solution, 7 parts of zircon powder and 3 parts of aluminum hydroxide.
As a preferred technical scheme of the invention: the raw materials comprise the following components in parts by weight: 100 parts of polysiloxane, 60 parts of tetraethoxysilane, 3 parts of rutile titanium dioxide, 6 parts of xylene, 15 parts of sulfuric acid, 50 parts of polyurethane acrylate, 3 parts of polyether, 25 parts of 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, 12 parts of alkyl phosphate diethanol amine salt, 13 parts of cuprous oxide, 6 parts of chromium oxide, 15 parts of ethyl acetate, 5 parts of cobalt naphthenate solution, 20 parts of aluminum powder, 20 parts of graphene dispersion solution, 5 parts of zircon powder and 2 parts of aluminum hydroxide.
As a preferred technical scheme of the invention: the purity of the zircon powder is more than or equal to 99.8 percent, and the granularity is 1-20 mu m.
As a preferred technical scheme of the invention: and grinding and dispersing in the third step to the fineness of less than or equal to 20 mu m.
As a preferred technical scheme of the invention: the thickness of the spraying in the fourth step is 0.01-0.1 mm.
As a preferred technical scheme of the invention: the baking time in the fourth step is 2-3 h.
Compared with the prior art, the preparation method of the satellite outer surface heat-insulating coating has the following technical effects: 1. the raw material source is wide, the cost is low, the storage period is 1-2 years, the solid content is 70-80%, and the high temperature of 250-; 2. All the components have a synergistic effect, the acid resistance is good, the 10 percent nitric acid is not foamed or dropped after 7-9d, the radiation coefficient En is more than or equal to 0.85, the wear resistance is excellent, and the flexibility is 1-3 mm; 3. the paint has the advantages of aviation lubricant resistance for 4-8 months, good conductivity, excellent heat-insulating property, low impurity content and plump and bright paint film; 4. the gasoline has the advantages of low dosage, high efficiency, energy conservation, accurate preparation, synergistic effect among all components, excellent electrical performance, capability of being widely used in various extreme environments, low probability of fatigue after long-term work in high-temperature environments, convenience in use, aviation-resistant gasoline, simple process, wide production and continuous replacement of the existing materials.
Detailed Description
The following is a more detailed description of embodiments of the invention:
example 1:
the first step is as follows: weighing the following components in parts by weight: 100 parts of polysiloxane, 50 parts of tetraethoxysilane, 1 part of rutile titanium dioxide, 4 parts of dimethylbenzene, 10 parts of sulfuric acid, 40 parts of urethane acrylate, 1 part of polyether, 15 parts of 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, 8 parts of alkyl phosphate diethanol amine salt, 11 parts of cuprous oxide, 4 parts of chromium oxide, 10 parts of ethyl acetate, 3 parts of cobalt naphthenate solution, 10 parts of aluminum powder, 10 parts of graphene dispersion solution, 2 parts of zircon powder and 1 part of aluminum hydroxide, wherein the purity of the zircon powder is more than or equal to 99.8%, and the granularity is 1 mu m.
The second step is that: polysiloxane, tetraethoxysilane, rutile titanium dioxide, xylene and sulfuric acid are put into a reaction kettle with a thermometer, a heating device and a stirring device, stirred for 30min at 30 ℃, the stirring speed is 80 r/min, then the temperature is raised to 50 ℃, polyurethane acrylate, polyether, 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, alkyl phosphate diethanol amine salt, cuprous oxide and chromium oxide are added, the stirring is continued for 30min, and the stirring speed is 90 r/min.
The third step: heating to 60 ℃, adding ethyl acetate, cobalt naphthenate solution, aluminum powder and graphene dispersion, stirring for 40min at a stirring speed of 100 r/min, heating to 70 ℃, adding the rest raw materials, stirring for 50min at 200 r/min, stirring completely, then putting into a grinder to grind for 48h, and grinding and dispersing to a fineness of less than or equal to 20 microns;
the fourth step: grinding uniformly, constructing by a spraying method, wherein the spraying thickness is 0.01mm, drying for 10min after spraying, baking at 200 ℃, and curing to form a film, wherein the baking time is 2 h.
The raw materials have wide sources and low cost, the storage period is 1 year, the solid content is 70 percent, and the high temperature of 250 ℃ is resisted; the components have a synergistic effect, the acid resistance is good, the 10% nitric acid 7d does not foam or fall off, the radiation coefficient En is more than or equal to 0.85, the wear resistance is excellent, and the flexibility is 3 mm; the paint has the advantages of aviation lubricant resistance for 4 months, good conductivity, excellent heat-insulating property, low impurity content and plump and bright paint film; the gasoline has the advantages of low dosage, high efficiency, energy conservation, accurate preparation, synergistic effect among all components, excellent electrical performance, capability of being widely used in various extreme environments, low probability of fatigue after long-term work in high-temperature environments, convenience in use, aviation-resistant gasoline, simple process, wide production and continuous replacement of the existing materials.
Example 2:
the first step is as follows: weighing the following components in parts by weight: 100 parts of polysiloxane, 70 parts of tetraethoxysilane, 5 parts of rutile titanium dioxide, 8 parts of dimethylbenzene, 20 parts of sulfuric acid, 60 parts of polyurethane acrylate, 5 parts of polyether, 35 parts of 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, 16 parts of alkyl phosphate diethanol amine salt, 15 parts of cuprous oxide, 8 parts of chromium oxide, 20 parts of ethyl acetate, 7 parts of cobalt naphthenate solution, 30 parts of aluminum powder, 30 parts of graphene dispersion liquid, 7 parts of zircon powder and 3 parts of aluminum hydroxide, wherein the purity of the zircon powder is more than or equal to 99.8%, and the granularity of the zircon powder is 20 microns.
The second step is that: polysiloxane, tetraethoxysilane, rutile titanium dioxide, xylene and sulfuric acid are put into a reaction kettle with a thermometer, a heating device and a stirring device, stirred for 50min at 40 ℃, the stirring speed is 100 r/min, then the temperature is raised to 60 ℃, polyurethane acrylate, polyether, 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, alkyl phosphate diethanol amine salt, cuprous oxide and chromium oxide are added, and the mixture is continuously stirred for 40min, and the stirring speed is 110 r/min.
The third step: heating to 70 ℃, adding ethyl acetate, cobalt naphthenate solution, aluminum powder and graphene dispersion, stirring for 50min at a stirring speed of 200 r/min, heating to 80 ℃, adding the rest raw materials, stirring for 60min at 300 r/min, stirring completely, then putting into a grinder to grind for 50h, and grinding and dispersing to a fineness of less than or equal to 20 microns;
the fourth step: grinding uniformly, constructing by a spraying method, wherein the spraying thickness is 0.1mm, drying for 30min after spraying, baking at 220 ℃, and curing to form a film, wherein the baking time is 3 h.
The raw materials have wide sources and low cost, the storage period is 1 year, the solid content is 75 percent, and the high temperature of 350 ℃ is resisted; all components have a synergistic effect, the acid resistance is good, 10% nitric acid is not foamed or falls off after 8d, the radiation coefficient En is more than or equal to 0.85, the wear resistance is excellent, and the flexibility is 2 mm; the aviation-resistant lubricating oil has the advantages of 6 months, good electrical conductivity, excellent heat-insulating property, low impurity content and plump and bright paint film; the gasoline has the advantages of low dosage, high efficiency, energy conservation, accurate preparation, synergistic effect among all components, excellent electrical performance, capability of being widely used in various extreme environments, low probability of fatigue after long-term work in high-temperature environments, convenience in use, aviation-resistant gasoline, simple process, wide production and continuous replacement of the existing materials.
Example 3:
the first step is as follows: weighing the following components in parts by weight: 100 parts of polysiloxane, 60 parts of tetraethoxysilane, 3 parts of rutile titanium dioxide, 6 parts of xylene, 15 parts of sulfuric acid, 50 parts of polyurethane acrylate, 3 parts of polyether, 25 parts of 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, 12 parts of alkyl phosphate diethanol amine salt, 13 parts of cuprous oxide, 6 parts of chromium oxide, 15 parts of ethyl acetate, 5 parts of cobalt naphthenate solution, 20 parts of aluminum powder, 20 parts of graphene dispersion solution, 5 parts of zircon powder and 2 parts of aluminum hydroxide, wherein the purity of the zircon powder is more than or equal to 99.8%, and the granularity of the zircon powder is 10 mu m.
The second step is that: polysiloxane, tetraethoxysilane, rutile titanium dioxide, xylene and sulfuric acid are put into a reaction kettle with a thermometer, a heating device and a stirring device, stirred for 40min at 35 ℃, the stirring speed is 90 r/min, then the temperature is raised to 55 ℃, polyurethane acrylate, polyether, 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, alkyl phosphate diethanol amine salt, cuprous oxide and chromium oxide are added, and the mixture is continuously stirred for 35min, and the stirring speed is 100 r/min.
The third step: heating to 65 ℃, adding ethyl acetate, cobalt naphthenate solution, aluminum powder and graphene dispersion, stirring for 45min at a stirring speed of 150 r/min, heating to 75 ℃, adding the rest raw materials, stirring for 55min at 250 r/min, stirring completely, then putting into a grinder to grind for 49h, and grinding and dispersing to a fineness of less than or equal to 20 microns;
the fourth step: grinding uniformly, constructing by a spraying method, wherein the spraying thickness is 0.05mm, drying for 20min after spraying, baking at 210 ℃, and curing to form a film, wherein the baking time is 2.5 h.
The raw materials have wide sources and low cost, the storage period is 2 years, the solid content is 80 percent, and the high temperature of 450 ℃ is resisted; the components have a synergistic effect, the acid resistance is good, 10% nitric acid 9d does not foam or fall off, the radiation coefficient En is more than or equal to 0.85, the wear resistance is excellent, and the flexibility is 1 mm; the paint has the advantages of aviation lubricant resistance for 8 months, good conductivity, excellent heat-insulating property, low impurity content and plump and bright paint film; the gasoline has the advantages of low dosage, high efficiency, energy conservation, accurate preparation, synergistic effect among all components, excellent electrical performance, capability of being widely used in various extreme environments, low probability of fatigue after long-term work in high-temperature environments, convenience in use, aviation-resistant gasoline, simple process, wide production and continuous replacement of the existing materials.
While the embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (5)
1. A preparation method of a satellite outer surface heat insulation coating is characterized by comprising the following steps: the first step is as follows: weighing 100 parts of polysiloxane, 60 parts of tetraethoxysilane, 3 parts of rutile titanium dioxide, 6 parts of xylene, 15 parts of sulfuric acid, 50 parts of urethane acrylate, 3 parts of polyether, 25 parts of 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, 12 parts of alkyl phosphate diethanol amine salt, 13 parts of cuprous oxide, 6 parts of chromium oxide, 15 parts of ethyl acetate, 5 parts of cobalt naphthenate solution, 20 parts of aluminum powder, 20 parts of graphene dispersion solution, 5 parts of zircon powder and 2 parts of aluminum hydroxide according to the mass part ratio of the components; the second step is that: putting polysiloxane, tetraethoxysilane, rutile titanium dioxide, xylene and sulfuric acid into a reaction kettle with a thermometer, a heating device and a stirring device, stirring for 30-50min at 30-40 ℃, stirring at 80-100 r/min, heating to 50-60 ℃, adding urethane acrylate, polyether, 2- (2' -hydroxy-3 ',5' -di-tert-butylphenyl) -benzotriazole, alkyl phosphate diethanol amine salt, cuprous oxide and chromium oxide, and continuously stirring for 30-40min at 90-110 r/min; the third step: heating to 60-70 ℃, adding ethyl acetate, cobalt naphthenate solution, aluminum powder and graphene dispersion, stirring for 40-50min at the stirring speed of 100-; the fourth step: grinding uniformly, constructing by a spraying method, drying for 10-30min after spraying, baking at 200-220 ℃, and solidifying into a film.
2. The preparation method of the satellite external surface thermal insulation coating according to claim 1, characterized in that: the purity of the zircon powder is more than or equal to 99.8 percent, and the granularity is 1-20 mu m.
3. The preparation method of the satellite external surface thermal insulation coating according to claim 1, characterized in that: and grinding and dispersing in the third step to the fineness of less than or equal to 20 mu m.
4. The preparation method of the satellite external surface thermal insulation coating according to claim 1, characterized in that: the thickness of the spraying in the fourth step is 0.01-0.1 mm.
5. The preparation method of the satellite external surface thermal insulation coating according to claim 1, characterized in that: the baking time in the fourth step is 2-3 h.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811179242.6A CN109337575B (en) | 2018-10-10 | 2018-10-10 | Preparation method of satellite outer surface heat-insulating coating |
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