CN115521695B - High-temperature-resistant corrosion-resistant light coating and preparation method and application thereof - Google Patents
High-temperature-resistant corrosion-resistant light coating and preparation method and application thereof Download PDFInfo
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Abstract
The invention provides a high-temperature-resistant anti-corrosion light coating which is prepared from silicon dioxide hollow microspheres, lithium silicate, alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide, nano zinc borate, sulfobetaine, hydroxyethyl methacrylate, nano aluminum silicate fiber, waterborne polyurethane and a surfactant AFCONA-5071. The high-temperature-resistant anti-corrosion light coating for the unmanned aerial vehicle has excellent heat insulation effect, and when the thickness of the obtained coating is 0.08mm, the temperature of a coating substrate can be not higher than 50 ℃ within 15 minutes at 1300 ℃, and meanwhile, the coating has better anti-corrosion and anti-scraping functions.
Description
Technical Field
The invention belongs to the technical field of functional coatings, and particularly relates to a high-temperature-resistant corrosion-resistant light coating, a preparation method and application thereof.
Background
With the continuous development of new industrial technologies such as artificial intelligence technology, advanced communication technology, high-end imaging technology, advanced detection technology and the like, industrial equipment gradually gets rid of the fence of the traditional working environment, and provides a foundation for people to further realize unmanned related work and improve the working conditions of related industries.
The new working environment generally means more extreme conditions, such as high temperature, high wind, dense smoke, and corrosive environments, etc., than the traditional working environment of the equipment. Thus, the higher the requirements of the new working environment on the device are often.
Unmanned aerial vehicle is the novel productivity instrument that collects the above-mentioned emerging industry technique as an organic whole, has obtained extensive application in aspects such as shooting, survey and drawing, agriculture, but when using in these fields, basically need not unmanned aerial vehicle face extreme environment such as high temperature, dense smoke.
With the continuous improvement of the requirements on the working environment of the unmanned aerial vehicle, people research the influence of the high-temperature environment on the unmanned aerial vehicle. Liliang (plum) [1] And the problems of thermal damage of the unmanned aerial vehicle in a fire scene environment are researched, the main forms of thermal radiation and thermal convection of the fire scene are proposed, the thermal damage of a fuselage can be increased when the relative distance between the unmanned aerial vehicle and flame is reduced, and the safety example of the unmanned aerial vehicle flying in the fire scene is 0.8 meter. Li Niansai [2] And the like, the research shows that the influence of the high-temperature environment on the battery performance is more than 50 ℃, and when the environment temperature exceeds 50 ℃, the battery temperature cannot be well controlled. These studies indicate that the high temperature environment has a great influence on the unmanned aerial vehicle body and the battery, and the unmanned aerial vehicle is limited to work in the high temperature environment.
Fire extinguishment is a typical high temperature environmental operation since 1972 the first time the world was filed in Germany with unmanned aerial vehicle extinguishment patents [3] How to utilize unmanned aerial vehicle to better participate in fire-fighting work is always concerned by people. However, many factors restricting the further development of unmanned aerial vehicles in the fire-fighting field are still more, and many problems need to be solved. Wherein, designing corresponding materials, reducing the quality of the unmanned aerial vehicle and improving the temperature resistance of the unmanned aerial vehicle are one of the problems to be solved urgently [4] 。
The research on the temperature-resistant coating technology is an important way for providing high temperature resistance for corresponding equipment. Although some high-temperature-resistant coating technologies have been developed in the aerospace field, the technologies are either in a secret state due to the characteristics of military use or very high in cost, so that a fire-fighting unmanned aerial vehicle is still in a state of lacking a high-temperature-resistant coating for availability, and the inventor of the patent searches on the China know network by taking an unmanned aerial vehicle, fire protection and high temperature resistance as search words, and does not find reports of the unmanned aerial vehicle which can enter a fire-fighting environment for working.
As one of the new aircraft, unmanned aerial vehicles can be referred to the existing aircraft coating technology for research on their coating materials. Sun Zhe [5] The aerospace coatings are reviewed by the et al, the summary of related researches on heat-insulating ablation-resistant protective coatings is included, the research on high-temperature resin which can resist the temperature of more than 600 ℃ and the lack of products in China are pointed out, and the more urgent is the requirement on coating materials which can resist the temperature of 800-1200 ℃ and have heat-insulating/ablation-resistant functions. As the unmanned aerial vehicle for fire control belongs to the field of fire control, the research on the coating material of the unmanned aerial vehicle for fire control can also refer to the traditional fire-fighting material technology, such as flame-retardant material and heat-insulating material [6] 。
However, to the knowledge of the inventors of the present patent, existing coatings are also difficult to use for fire fighting robots that can access a fire scene. The possible reasons are that in a fire scene, the temperature is generally 400-600 ℃, and can even reach more than 1300 DEG C [7] While the precision instruments and batteries inside the drone are often difficult to withstand operating temperatures above 50 ℃, the development of drone coatings that can access fire has been slow.
Even so, the existing high-temperature-resistant coating research reports that the heat insulation mechanism and the corresponding technical scheme have reference significance. In terms of heat insulation, a few technical schemes are to add a filler (such as hollow microbeads) with high porosity into a coating system [8-10] This approach may allow heat to be conducted through air, thereby reducing the thermal conductivity of the coating, but these approaches are generally only suitable for use in temperature environments below 400 ℃; other schemes, which use silicon carbide as the material, continuously collide with the lattice and bond clusters by the energy of molecular vibration and rotation to re-emit the absorbed heat back to the environment [11-13] And transition metal oxides (e.g., coO, cuO) [14-15] The method comprises the steps of carrying out a first treatment on the surface of the Still other solutions provide thermal insulation by reflecting radiation, and the materials chosen are typically TiO2, znO pigments with a high whiteness. Therefore, when researching unmanned aerial vehicle coating which can enter a fire scene, the corresponding materials can be selected by referring to the heat insulation mechanism and the respective technical scheme thereof. At the same time, the materials selected are as existing as possible, taking into account cost issues.
In addition to the technical difficulties and development requirements brought by the high temperature environment, flying chips caused by deflagration often appear in the fire scene, and the flying chips are extremely easy to scratch the coating, so that the high temperature resistance of the coating is drastically reduced.
In view of the foregoing, there is a need in the art to develop unmanned aerial vehicle coatings that can meet the requirements of operating at fire temperatures, so that the coatings can operate in a 1300 ℃ environment, ensure that unmanned aerial vehicles within the coatings can operate in a working environment at temperatures no higher than 50 ℃ for a longer period of time, and have certain scratch resistance to effectively cope with flying debris during deflagration.
The documents cited in this section are as follows:
[1] liliang, liu Xiaoyong, xu Jianjiang, et cetera unmanned aerial vehicle thermal injury test research under fire scene [ J ]. National science journal of security, 31 (2): 7.
[2] Li Niansai, liu Xiaoyong, liliang, etc. unmanned aerial vehicle lithium ion battery high and low temperature extreme environmental adaptability research [ J ]. Chinese safety science journal, 30 (8): 6.
[3] Wang Shan, guanjialin. Fire fighting unmanned aerial vehicle technical review [ J ]. Henna technology 2020, v.39; no.722 (24): 135-138.
[4] Li Jianyou, shui Feng, zhang Saiyu. Application overview of unmanned aerial vehicle in forest fire control field [ J ]. Forest fire prevention, 2018,000 (001): 45-49.
[5] Sun Zhe, yangkang, ma Hong, et al, aviation and aerospace coatings present and future developments [ J ]. Chinese coatings, 2019,034 (001): 28-32.
[6] Ji Yuhong, zhang Guoliang, xia Jinyang, et al technical progress of thermal insulation coatings [ J ]. Coating industry, 2019,049 (003): 80-87.
[7] How far is there a fire to be afraid of a group renting room? The temperature rises 1300 ℃ J at room temperature for 10 minutes, and the safety and health are 2018,000 (002): 9-10.
[8]Bao Y,Kang Q L,Ma J Z,et al.Monodisperse Hollow TiO2Spheres for Thermal Insulation Materials:Template-Free Synthesis,Characterization and Properties[J].Ceramics International,2017:S0272884217305357.
[9] Wu Guodong preparation of silica Heat insulation coating and characterization of properties [ D ]. Harbin university of industry.
[10] Xu Yongquan, guo Xingzhong, hong Louying A heat insulating coating containing hollow silica microspheres and its use, CN110157315A [ P ].
[11] Wu Haihua, peng Jianhui, reret, etc. A graphite/silicon carbide heat-insulating backing and its preparation method, CN108675790A [ P ].
[12] A composite heat-insulating silicon dioxide coating for the primary and secondary strong light, fan Li and its preparing process, CN106082777A P.
[13]Zhang B,Tong Z,Yu H,et al.Flexible and high-temperature resistant ZrO 2/SiC-based nanofiber membranes for hightemperature thermal insulation[J].Journal ofAlloys and Compounds,2021.
[14]Yao Q,Jia J,Chen T,et al.High temperature tribological behaviors and wear mechanisms of NiAl-MoO3/CuO composite coatings[J].Surface and Coatings Technology,2020,395:125910.
[15] Yi Jianlong, zhang Xinming, gu Rui, etc. the high temperature and corrosion resistance of ceria-yttria stabilized zirconia coatings on magnesium rare earth alloys [ J ]. Material protection, 2010,43 (8): 14-16.
Disclosure of Invention
Aiming at the defects of the prior art and the requirement on the unmanned aerial vehicle coating capable of working in a high-temperature environment, the application aims at providing the high-temperature-resistant and corrosion-resistant light coating for the unmanned aerial vehicle. The unmanned aerial vehicle coating can ensure that unmanned aerial vehicle components in the coating can obtain a working environment which is not higher than 50 ℃ within 15 minutes at the temperature of 1300 ℃; meanwhile, the paint also has the advantages of light weight, corrosion resistance and scratch resistance.
In order to achieve the above purpose, the technical scheme adopted in the application is as follows:
the high-temperature-resistant anti-corrosion light coating for the unmanned aerial vehicle comprises a component A, a component B and a component C as raw materials;
the weight portions are as follows:
the component A comprises 10-30 parts of silicon dioxide hollow microspheres and 5 parts of lithium silicate;
the component B comprises 30-40 parts of nano oxide mixture and 1 part of surfactant AFCONA-5071;
the components in the component C comprise 20-30 parts of sulfobetaine, 3-5 parts of hydroxyethyl methacrylate, 1-2 parts of nano aluminum silicate fiber and 40-50 parts of waterborne polyurethane;
the nano oxide mixture consists of nano yttrium oxide, alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide and nano zinc borate in the weight ratio of (2-3): (4-6): (7-8): (2-3): (2-3): (1-2).
In the aspect of preparing the heat-insulating coating, the hollow silicon dioxide is a common substance, has high internal porosity and low air content, has good barrier effect on conduction and convection, and can play a role in heat insulation. Similar materials are expanded polystyrene, aerogel, expanded perlite, and the like. In general, coatings with hollow silica as the primary insulating material have a relatively limited insulating effect, and are generally only useful in low temperature conditions (normal to 200 ℃) and a few expanded perlite based coatings are useful in medium temperature conditions (200 to 500 ℃).
The lithium silicate is also called lithium water glass, has better permeability, moldability and heat resistance, and is also commonly used as a raw material in the aspect of preparing a heat-insulating coating [16-17] . The temperature resistance of the coating using lithium silicate as the raw material is only hundreds of DEG C at present, and not to mention that the coating can realize good heat insulation effect in thousands DEG C environment, and the coating has far distance from the performance of the coating required by the invention. Yttria is commonly used in air spray insulation materials [18-19] Also useful for preparing ablation resistant coatings [20-21] . According to the invention, in the early stage of research, the heat insulation performance of the coating can be greatly improved by selecting the lithium silicate and the nano yttrium oxide on the basis of the silicon dioxide hollow microspheres, and the synergistic effect is possibly found by the heat insulation blocking effect of the silicon dioxide hollow microspheres and the radiation heat insulation effect of the yttrium oxide and the lithium silicate. The present invention is based on the finding that the preparation of coatings which meet the object of the invention has been explored.
Based on this, the inventors mixed other common transition metal oxides with nano yttrium oxide to examine the change of the heat-insulating property of the obtained coating. Unfortunately, no matter whether the nano iron oxide, the nano copper oxide or the nano cobalt oxide is mixed with the nano yttrium oxide, the influence on the heat insulation performance of the coating is not obvious. Through continuous fumbling, the inventor finds that after alpha-phase nano alumina, gamma-phase nano alumina, nano magnesia and nano zinc borate are mixed with nano yttrium oxide, the heat insulation performance of the coating is greatly improved compared with the heat insulation performance of the coating only added with nano yttrium oxide. This suggests that hollow silica microspheres, lithium silicate and mixtures of the above nano-oxides are critical in coating systems aimed at solving the technical object of the present invention.
The influence of other system substances is further examined, and the addition of the sulfobetaine is found to further improve the heat insulation performance of the coating. However, in a system with only nano yttrium oxide, the addition of sulfobetaine does not greatly improve the heat insulation performance of the coating. This suggests that the sulfobetaines are likely to have some dispersion in the mixed nano-oxide system, so that the individual nano-oxides are more uniformly dispersed in the coating. In addition, in other existing temperature resistant coatings, the nano oxide is replaced by the nano oxide compound disclosed by the invention, and the effect of the temperature resistant coating is basically not influenced. This suggests that the use of nano-oxides in radiation insulation is likely to be affected by the interaction of different nano-oxides and may also be limited by the combination of other coating materials. Generally, hollow microspheres can provide voids for the coating, and such air can create a near vacuum environment under certain conditions to effectively block heat; when the external temperature is too high, deformation can occur in the coating, and the deformation is sometimes beneficial to adhesion of low-melting-point substances and other components, so that the cadmium temperature effect is improved. When the heat insulation and radiation heat insulation effects are collectively achieved in a synergistic effect, a higher heat insulation effect can be obtained. The hollow silica microspheres, lithium silicate and selected nano-oxide mixtures of the present invention are likely to exhibit significant synergy in thermal insulation and radiation insulation.
It is worth noting that the scratch problem caused by deflagration flying chips is always solved in the research process of the invention. The inventors found that the addition of hydroxyethyl methacrylate and nano aluminum silicate fibers is very important.
In the research process, the inventor of the invention also considers the problems of corrosion resistance and light weight of the unmanned aerial vehicle, and based on the silicon dioxide hollow microsphere-lithium silicate-nano oxide mixture core component system, the inventor finds that the corrosion resistance and the lighter weight are not easy to obtain. The inventors have filed a patent for a coating that is resistant to high temperatures and corrosion and has a lighter weight, and will not be described in detail herein.
As a preferable technical scheme of the invention, the component C also comprises 10-15 parts of aqueous polyaspartic acid ester. The preferred solution allows to obtain a higher temperature resistance, in particular at 1300 ℃, a maintenance time of 17 minutes at a temperature of not higher than 50 ℃ for the substrate within the coating. The film forming material can form new active center at the fracture under high temperature environment, can further react with other components to form film again, and improves the temperature resistance. The matching of the aqueous polyaspartic acid ester and the aqueous polyurethane has better effect on the film formation and the action with other components.
As a preferred technical scheme of the present invention, the nano-oxide mixture further comprises nano-cerium oxide and nano-zinc oxide having the same weight as the nano-zinc borate. In this preferred embodiment, the maintenance time can be extended to 18 minutes in the presence of an aqueous polyaspartate.
As an implementation technical scheme of the invention, in the nano oxide mixture, the particle size of each nano oxide is 100-200 nm.
As a preferable technical scheme of the invention, the particle size of the alpha-phase nano alumina, the gamma-phase nano alumina and the nano silica is 100-150 nm, and the particle size of the nano yttrium oxide, the nano magnesium oxide and the nano zinc borate is 150-200 nm.
According to the preferred technical scheme, the silica hollow microsphere comprises, by weight, 20 parts of silica hollow microspheres, 35 parts of nano oxide mixture, 26 parts of sulfobetaine, 4 parts of hydroxyethyl methacrylate, 2 parts of nano aluminum silicate fibers and 48 parts of waterborne polyurethane.
It is another object of the present invention to provide a method for preparing the above coating, wherein the components are uniformly mixed, and water is added and stirred during mixing. The method specifically adopted is as follows: mixing the components according to the weight parts of the components in the component B, adding deionized water, and uniformly stirring at 1000-1500 rpm/min at 50-60 ℃; then adding component C, stirring at 70-95 deg.C and 1000-1500 rpm/min, finally adding component A, stirring at 50-60 deg.C and 2000-2500 rpm/min uniformly to obtain the invented product.
It is also an object of the present invention to provide the use of the above coating as a coating for unmanned aerial vehicles. It is particularly pointed out that, when used as a coating, the coating can have a thickness of only within 0.1mm, and the excellent high temperature resistance can be obtained. As shown in the examples of the present invention, the thickness used in the corresponding test was 0.08mm.
The invention has the beneficial effects that:
the high-temperature-resistant anti-corrosion light coating for the unmanned aerial vehicle has excellent heat insulation effect, and when the thickness of the obtained coating is 0.08mm, the temperature of a coating substrate can be not higher than 50 ℃ within 15 minutes at 1300 ℃, and meanwhile, the coating has better anti-corrosion and anti-scraping functions.
The literature cited in this section:
[16] chen Qiuxia lithium silicate aqueous coating and high temperature resistant coating research [ D ] university of Nanchang.
[17] Huang Chuanfeng, minru, zhang Dandan, etc. preparation and performance study [ J ] Shandong chemical engineering, 2019,048 (021): 6-8.
[18] Ma Zhuang, li Xing, liu Ling, et al, preparation of NiCr2O4/YSZ composite coating and heat insulation research [ J ] New technology, 2018.
[19] Wang Le, li Taijiang, li Yong, and the like 45 steel surface atmospheric plasma sprayed yttria partially stabilized zirconia thermal barrier coating and its performance [ J ]. Material protection, 2014 (10).
[20] Yang Lingfang, huang Zhi, zhang Rong a method for improving the high temperature and corrosion resistance properties of a thermal barrier coating, CN112962050A [ P ].
[21] Zhao Yongxun and Zhao Zhi A process for preparing high-temp. resistant coating composite material, CN104311146A P.
Drawings
FIG. 1 is a chart showing the thermal insulation performance test and thermogram of example 7 of the present invention.
Detailed Description
The present invention is described in detail below by way of examples, which are necessary to be pointed out herein for further illustration of the invention and are not to be construed as limiting the scope of the invention, since numerous insubstantial modifications and adaptations of the invention will occur to those skilled in the art in light of the foregoing disclosure.
In the following experiments, the experimental raw materials and the experimental methods adopted are as follows:
experimental raw materials:
silica hollow microspheres: the laboratory is self-owned, and the grain diameter is 200-300 nm;
nanometer yttrium oxide, alpha-phase nanometer aluminum oxide, gamma-phase nanometer aluminum oxide, nanometer magnesium oxide, nanometer silicon dioxide, nanometer zinc borate, nanometer ferric oxide, nanometer copper oxide and nanometer cobalt oxide: the particle size of alpha-phase nano alumina, gamma-phase nano alumina and nano silica is 100-150 nm, and the particle size of nano yttrium oxide, nano magnesium oxide, nano zinc borate, nano iron oxide, nano copper oxide and nano cobalt oxide is 150-200 nm;
lithium silicate, wollastonite powder, kaolin: purchased from Jinan Sheng and chemical Co., ltd
Sulfobetaines, hydroxyethyl methacrylate, polyaspartic acid ester: laboratory self-contained aqueous polyurethane: prepared by reference (DOI: 10.19319/j. Cnki. Isn.1008-021x.2019.21.003)
Surfactant AFCONA-5071: test method purchased from Shanghai Baiyin chemical Co., ltd.:
thermal insulation performance test: and fixing a blast lamp, aligning flame to the center of the sample, vertically flushing flame flow onto the sample, and simultaneously using an infrared thermometer to test the back temperature of the tinplate.
Hardness measurement: the hardness of the coating was measured according to GB/T6739-2006 pencil test for hardness of coating film.
Scratch resistance test: and (3) loading a 500g weight on one side of the sand-containing scouring pad, repeatedly scratching the surface of the coating at a certain speed, and representing the scratch resistance of the coating by using the maximum number of times without leaving obvious scratches.
Heat resistance test
Placing the sample in a muffle furnace, heating to 1300 ℃ at 10 ℃/min, preserving heat for 2 hours, standing and cooling, and observing and recording whether the coating generates phenomena of delamination, peeling, bubbling, cracking and the like after cooling to room temperature (25 ℃). The coating substrate is a ceramic substrate.
Neutral salt spray test was performed: according to GB/T1771-2007, coating to be tested is sprayed on the front and back surfaces of the test plate, sealing treatment is carried out on edges by using paraffin after solidification, and the integrity of the coating is observed after a certain period of time.
Example 1
The preparation method comprises the following steps of:
20 parts of silicon dioxide hollow microspheres, 5 parts of lithium silicate, 35 parts of nano oxide mixture, 1 part of surfactant AFCONA-5071, 26 parts of sulfobetaine, 4 hydroxyethyl methacrylate, 2 parts of nano aluminum silicate fiber and 48 aqueous polyurethane;
the nano oxide mixture consists of nano yttrium oxide, alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide and nano zinc borate, and the weight ratio is 2:5:7:2:2:1.
mixing the nano oxide mixture and a surfactant AFCONA-5071, adding deionized water (the solid-liquid ratio is 50-55%, and other embodiments are the same), and stirring at 1500rpm/min for 30min at 55 ℃; then adding sulfobetaine, hydroxyethyl acrylate, nano aluminum silicate fiber and waterborne polyurethane, and stirring at 1500rpm/min for 20min at 90 ℃; finally, adding the silicon dioxide hollow microspheres and lithium silicate, stirring at 2500rpm/min for 30min at 55 ℃, and coating.
Example 2
The preparation method comprises the following steps of:
10 parts of silicon dioxide hollow microspheres, 5 parts of lithium silicate, 30 parts of nano oxide mixture, 1 part of surfactant AFCONA-5071, 20 parts of sulfobetaine, 3 hydroxyethyl methacrylate, 1 part of nano aluminum silicate fiber and 40 aqueous polyurethane;
the nano oxide mixture consists of nano yttrium oxide, alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide and nano zinc borate, and the weight ratio is 2.5:4:8:3:3:2.
mixing the nano oxide mixture and a surfactant AFCONA-5071, adding deionized water, and stirring at 1500rpm/min for 30min at 55 ℃; then adding sulfobetaine, hydroxyethyl acrylate, nano aluminum silicate fiber and waterborne polyurethane, and stirring at 1500rpm/min for 20min at 90 ℃; finally, adding the silicon dioxide hollow microspheres and lithium silicate, stirring at 2500rpm/min for 30min at 55 ℃, and coating.
Example 3
The preparation method comprises the following steps of:
30 parts of silicon dioxide hollow microspheres, 5 parts of lithium silicate, 40 parts of nano oxide mixture, 1 part of surfactant AFCONA-5071, 30 parts of sulfobetaine, 5 parts of hydroxyethyl methacrylate, 2 parts of nano aluminum silicate fiber and 50 parts of waterborne polyurethane;
the nano oxide mixture consists of nano yttrium oxide, alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide and nano zinc borate, and the weight ratio is 3:6:7.5:2.5:2.5:1.5.
mixing the nano oxide mixture and a surfactant AFCONA-5071, adding deionized water, and stirring at 1500rpm/min for 30min at 55 ℃; then adding sulfobetaine, hydroxyethyl acrylate, nano aluminum silicate fiber and waterborne polyurethane, and stirring at 1500rpm/min for 20min at 90 ℃; finally, adding the silicon dioxide hollow microspheres and lithium silicate, stirring at 2500rpm/min for 30min at 55 ℃, and coating.
Example 4
The preparation method comprises the following steps of:
20 parts of silica hollow microspheres, 5 parts of lithium silicate, 30 parts of a nano oxide mixture, 1 part of a surfactant AFCONA-5071, 20 parts of sulfobetaine, 3 hydroxyethyl methacrylate, 1 part of nano aluminum silicate fiber, 40 parts of aqueous polyurethane and 12 parts of aqueous polyaspartic acid ester;
the nano oxide mixture consists of nano yttrium oxide, alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide and nano zinc borate, and the weight ratio is 2.5:4:8:3:3:2.
mixing the nano oxide mixture and a surfactant AFCONA-5071, adding deionized water, and stirring at 1500rpm/min for 30min at 55 ℃; then adding sulfobetaine, hydroxyethyl acrylate, nano aluminum silicate fiber, waterborne polyurethane and waterborne polyaspartic acid ester, and stirring at 1500rpm/min for 20min at 90 ℃; finally, adding the silicon dioxide hollow microspheres and lithium silicate, stirring at 2500rpm/min for 30min at 55 ℃, and coating.
Example 5
In comparison with example 4, the aqueous polyaspartic acid ester was 10 parts by weight, the remainder being identical to example 4.
Example 6
In comparison with example 4, the aqueous polyaspartic acid ester was 15 parts by weight, the remainder being identical to example 4.
Example 7
The preparation method comprises the following steps of:
20 parts of silica hollow microspheres, 5 parts of lithium silicate, 30 parts of a nano oxide mixture, 1 part of a surfactant AFCONA-5071, 20 parts of sulfobetaine, 3 hydroxyethyl methacrylate, 1 part of nano aluminum silicate fiber, 40 parts of aqueous polyurethane and 12 parts of aqueous polyaspartic acid ester;
the nano oxide mixture consists of nano yttrium oxide, alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide, nano zinc borate, nano cerium oxide and nano zinc oxide, and the weight ratio is 2.5:4:8:3:3:2:2:2.
mixing the nano oxide mixture and a surfactant AFCONA-5071, adding deionized water, and stirring at 1500rpm/min for 30min at 55 ℃; then adding sulfobetaine, hydroxyethyl acrylate, nano aluminum silicate fiber, waterborne polyurethane and waterborne polyaspartic acid ester, and stirring at 1500rpm/min for 20min at 90 ℃; finally, adding the silicon dioxide hollow microspheres and lithium silicate, stirring at 2500rpm/min for 30min at 55 ℃, and coating.
The above examples 1 to 7 were tested and the test results are shown in table 1:
TABLE 1
Note 1: in Table 1, when the heat insulating performance test was conducted, the outer flame temperature was 1300 to 1350 ℃, the coating thickness was 0.08mm, and the substrate was a tinplate (thickness 4.6 mm). The soak time is the time that the tin plate flat back temperature is maintained below 50 ℃ under flame alignment coating spray.
And (2) injection: in Table 1, the "apparent condition after ablation" indicates the heat resistance test result, and the smoothness indicates that the phenomena such as delamination, peeling, bubbling, cracking and the like were not generated, and the coating was in a smooth state.
The temperature change during the course of the experiment was recorded for example 7. As shown in FIG. 1, the temperature rose smoothly and slightly in the 0.5-4.5 minute period, and a larger rise (from 29.4 ℃ C. To 34.6 ℃ C.) occurred in the 4.5-5.5 minute period. Thereafter, at the 5.5-9 minute stage, a slightly larger but smooth trend of temperature rise stage (rise from 34.6 ℃ C. To 41.3 ℃ C.) was exhibited; then, at the 9-18 minute stage, a smooth small rise (rise from 41.3 ℃ C. To 49.8 ℃ C.) was exhibited; finally, in the 18-20.5 minute stage, a rapid heating trend is shown, and the temperature is rapidly increased from 49.8 ℃ to 100 ℃ in 2 minutes.
Comparative example 1
Before the technical schemes of examples 1-7 are obtained, other technical schemes are examined, and the representative technical schemes are as follows:
technical scheme 1-1:
the preparation method comprises the following steps of:
20 parts of silica hollow microspheres, 35 parts of wollastonite powder, 1 part of surfactant AFCONA-5071, 20 parts of kaolin and 40 parts of waterborne polyurethane;
stirring the above materials (500 rpm/min) uniformly to obtain the final product.
Technical solution 1-2
20 parts of silica hollow microspheres, 35 parts of lithium silicate, 1 part of surfactant AFCONA-5071, 20 parts of kaolin and 40 parts of waterborne polyurethane;
stirring the above materials (500 rpm/min) uniformly to obtain the final product.
Technical solutions 1 to 3
20 parts of silicon dioxide hollow microspheres, 35 parts of lithium silicate, 20 parts of nano yttrium oxide, 1 part of surfactant AFCONA-5071, 20 parts of kaolin and 40 parts of waterborne polyurethane;
stirring the above materials (500 rpm/min) uniformly to obtain the final product.
Technical solution 2-1
20 parts of silica hollow microspheres, 35 parts of lithium silicate, 20 parts of nano oxide mixture, 1 part of surfactant AFCONA-5071, 20 parts of kaolin and 40 parts of waterborne polyurethane;
stirring the above materials (500 rpm/min) uniformly to obtain the final product. The nano oxide mixture is prepared by mixing alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano zinc borate and nano yttrium oxide according to the weight ratio of 1:1:1:1:1.
Technical solution 2-2
20 parts of silica hollow microspheres, 35 parts of lithium silicate, 20 parts of nano oxide mixture, 1 part of surfactant AFCONA-5071, 20 parts of kaolin, 40 parts of waterborne polyurethane and 20 parts of sulfobetaine;
stirring the above materials (500 rpm/min) uniformly to obtain the final product. The nano oxide mixture is prepared by mixing alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano zinc borate and nano yttrium oxide according to the weight ratio of 1:1:1:1:1.
The above technical scheme was tested for heat insulating performance, the outer flame temperature was 400-420 ℃, the coating thickness was 0.1mm, the substrate was a tinplate (thickness 4.6 mm), and the results are shown in Table 2.
TABLE 2
Note that: in Table 2, the soak time is the time that the tin plate flat back temperature is maintained below 50 ℃ under flame-alignment coating spray.
Comparative example 2
Technical solution 3-1
Referring to the technical scheme 2-1 in comparative example 1, the nano-oxide mixture was replaced with a mixture of nano-yttrium oxide and nano-iron oxide in a weight ratio of 1:1.
Technical solution 3-2
Referring to the technical scheme 2-1 in comparative example 1, the nano-oxide mixture was replaced with a mixture of nano-yttrium oxide and nano-copper oxide in a weight ratio of 1:1.
Technical solution 3-3
Referring to the technical scheme 2-1 in comparative example 1, the nano-oxide mixture was replaced with a mixture of nano-yttrium oxide, nano-copper oxide and nano-cobalt oxide in a weight ratio of 1:1:1.
Technical solution 3-4
Based on the technical schemes 1-3, 20 parts of sulfobetaine are added.
According to the thermal insulation performance test method of comparative example 1, the thermal insulation time is not more than 350s.
Claims (9)
1. The high-temperature-resistant corrosion-resistant light coating is characterized in that the raw materials of the coating comprise a component A, a component B and a component C;
the weight portions are as follows:
the component A comprises 10-30 parts of silicon dioxide hollow microspheres and 5 parts of lithium silicate;
the component B comprises 30-40 parts of nano oxide mixture and 1 part of surfactant AFCONA-5071;
the components in the component C comprise 20-30 parts of sulfobetaine, 3-5 parts of hydroxyethyl methacrylate, 1-2 parts of nano aluminum silicate fiber and 40-50 parts of waterborne polyurethane;
the nano oxide mixture consists of nano yttrium oxide, alpha-phase nano aluminum oxide, gamma-phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide and nano zinc borate in the weight ratio of (2-3): (4-6): (7-8): (2-3): (2-3): (1-2);
in the nano oxide mixture, the particle size of each nano oxide is 100-200 nm; the particle size of the silica hollow microsphere is 200-300 nm.
2. The lightweight coating of claim 1, wherein the alpha phase nano alumina, gamma phase nano alumina and nano silica have a particle size of 100 to 150nm and the nano yttria, nano magnesia and nano zinc borate have a particle size of 150 to 200nm.
3. The light weight coating of claim 1, wherein component C further comprises 10 to 15 parts of an aqueous polyaspartic acid ester.
4. The lightweight coating of claim 3, wherein said nano-oxide mixture further comprises nano-cerium oxide in an amount by weight equivalent to nano-zinc borate and nano-zinc oxide in an amount by weight equivalent to nano-zinc borate.
5. The lightweight coating of claim 1, wherein the weight ratio of nano yttrium oxide, alpha phase nano aluminum oxide, gamma phase nano aluminum oxide, nano magnesium oxide, nano silicon dioxide, nano zinc borate is 2:5:7:2:2:1.
6. the lightweight coating of claim 1, wherein the silica hollow microspheres are 20 parts by weight, the nano-oxide mixture is 35 parts by weight, the sulfobetaine is 26 parts by weight, the hydroxyethyl methacrylate is 4 parts by weight, the nano-aluminum silicate fibers are 2 parts by weight, and the aqueous polyurethane is 48 parts by weight.
7. A method for preparing a high-temperature-resistant anti-corrosion light coating, which is characterized in that the high-temperature-resistant anti-corrosion light coating is the high-temperature-resistant anti-corrosion light coating according to any one of claims 1 to 6, and the preparation method is that the components are uniformly mixed, and water is added and stirred during mixing.
8. The preparation method according to claim 7, wherein the components are mixed according to the weight parts of the components in the component B, deionized water is added, and the mixture is stirred uniformly at 1000-1500 rpm at 50-60 ℃; then adding component C, stirring at 70-95 deg.C and 1000-1500 rpm, finally adding component A, stirring at 50-60 deg.C and 2000-2500 rpm uniformly to obtain the invented product.
9. Use of the high temperature resistant corrosion resistant light weight coating according to any one of claims 1 to 6 or the high temperature resistant corrosion resistant light weight coating prepared by the preparation method according to claim 7 or 8 as a unmanned aerial vehicle coating, characterized in that the thickness of the coating does not exceed 0.1mm.
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| WO2017073115A1 (en) * | 2015-10-27 | 2017-05-04 | 株式会社Ｉｎｕｉ | Coating liquid, composition for coating liquid, and refractory article having coating layer |
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| CN113831812A (en) * | 2021-09-16 | 2021-12-24 | 德爱威（中国）有限公司 | Environment-friendly scratch-resistant easy-to-clean interior wall coating and preparation method thereof |
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| WO2017073115A1 (en) * | 2015-10-27 | 2017-05-04 | 株式会社Ｉｎｕｉ | Coating liquid, composition for coating liquid, and refractory article having coating layer |
| CN108976964A (en) * | 2018-07-18 | 2018-12-11 | 安徽诺辰新型材料有限公司 | Nanometer heat isolation paint and preparation method thereof |
| CN112831252A (en) * | 2021-01-29 | 2021-05-25 | 烟台万华新材料技术有限公司 | Water-based high-temperature-resistant anticorrosive composition |
| CN113831812A (en) * | 2021-09-16 | 2021-12-24 | 德爱威（中国）有限公司 | Environment-friendly scratch-resistant easy-to-clean interior wall coating and preparation method thereof |
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