CN115521695A

CN115521695A - High-temperature-resistant anti-corrosion light coating and preparation method and application thereof

Info

Publication number: CN115521695A
Application number: CN202210546509.0A
Authority: CN
Inventors: 张凯; 刘清杰
Original assignee: Sichuan Aviation Vocational College Sichuan Space Advanced Technical School; Sichuan University
Current assignee: Sichuan Aviation Vocational College Sichuan Space Advanced Technical School; Sichuan University
Priority date: 2022-05-18
Filing date: 2022-05-18
Publication date: 2022-12-27
Anticipated expiration: 2042-05-18
Also published as: CN115521695B

Abstract

The invention provides a high-temperature-resistant anti-corrosion light coating which is prepared from hollow silica microspheres, lithium silicate, alpha-phase nano-alumina, gamma-phase nano-alumina, nano-magnesia, nano-silica, nano-zinc borate, sulfobetaine, hydroxyethyl methacrylate, nano-alumina silicate fibers, waterborne polyurethane and a surfactant AFCONA-5071 serving as raw materials. The high-temperature-resistant anti-corrosion light coating for the unmanned aerial vehicle has an excellent heat insulation effect, when the thickness of the obtained coating is 0.08mm, the temperature of a coating base material can be not higher than 50 ℃ for more than 15 minutes at 1300 ℃, and meanwhile, the light coating has good anti-corrosion and anti-scraping functions.

Description

High-temperature-resistant anti-corrosion light coating and preparation method and application thereof

Technical Field

The invention belongs to the technical field of functional coatings, and particularly relates to a high-temperature-resistant anti-corrosion light coating as well as a preparation method and application thereof.

Background

With the continuous development of the innovative industrial technologies such as artificial intelligence technology, advanced communication technology, high-end imaging technology and advanced detection technology, the industrial equipment gradually gets rid of the fence of the traditional working environment, and a foundation is provided for the human to further realize the unmanned operation and improve the working conditions of the related industries.

The new working environment generally implies more extreme conditions, such as high temperature, high wind, heavy smoke, corrosive environments, etc., relative to the conventional working environment of the equipment. Thus, new operating environments tend to place higher demands on the equipment.

Unmanned aerial vehicle is the novel productivity instrument that collects above-mentioned emerging industrial technology as an organic whole, has obtained extensive application in the aspect of shooting, survey and drawing, agriculture etc., nevertheless when these fields use, does not need unmanned aerial vehicle to face extreme environment such as high temperature, dense smoke basically.

Along with the continuous improvement of the requirement for the working environment of the unmanned aerial vehicle, people research the influence of the high-temperature environment on the unmanned aerial vehicle. Liliang (plum blossom) ^[1] The problem of thermal damage of the unmanned aerial vehicle in the fire scene environment is studied, the main forms of thermal damage of the unmanned aerial vehicle are heat radiation and heat convection in the fire scene, the reduction of the relative distance between the unmanned aerial vehicle and flame can increase the thermal damage of the body of the unmanned aerial vehicle, and the safety example that the unmanned aerial vehicle flies in the fire scene is indicated to be 0.8 m. Li Miss Si ^[2] The research shows that the influence of high-temperature environment on the battery performance is over 50 ℃, and when the environment temperature exceeds 50 ℃, the battery temperature cannot be well controlled. These researches show that the high temperature environment has great influence on the body or the battery of the unmanned aerial vehicle, and the unmanned aerial vehicle is limited to work in the high temperature environment.

Fire fighting was a typical high temperature environment and since 1972 a first global patent for fire fighting with unmanned aerial vehicles was filed in germany ^[3] How to utilize the better participation of unmanned aerial vehicle in the work of putting out a fire and putting out a fire of fire just receives people's attention always. However, at present, many factors restricting the further development of the unmanned aerial vehicle in the field of fire protection exist, and many problems need to be solved urgently. Wherein, designing corresponding materials, lightening the quality of the unmanned aerial vehicle and improving the temperature tolerance of the unmanned aerial vehicle are urgently needed to be solvedOne of the problems ^[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 confidential state due to the characteristics of military application or are very high in cost, so that the fire-fighting unmanned aerial vehicle still is in a state of lacking the availability of the high-temperature resistant coating.

As one of the new aircrafts, the unmanned aerial vehicle can refer to the existing aircraft coating technology for the research on the coating material thereof. Sun taimen ^[5] The people have reviewed the aviation and aerospace coatings, including the summary of relevant researches on the heat-insulating and ablation-resistant protective coatings, and point out that the demand of the coating materials which can resist the high temperature of more than 600 ℃ and have the heat-insulating/ablation-resistant functions is more urgent when the research on the high temperature resin which can resist the temperature of 800-1200 ℃ and the product shortage are carried out in China. As the fire-fighting unmanned aerial vehicle belongs to the field of fire fighting, the research on coating materials can refer to the traditional fire-fighting material technology, such as flame-retardant materials and heat-insulating materials ^[6] 。

However, according to the knowledge of the present patent inventors, existing coatings are also difficult to use for fire fighting drones that can enter the fire scene. The possible reason is that in a fire scene, the temperature is generally 400 to 600 ℃ and can even be as high as 1300 ℃ or higher ^[7] And the precise instruments and batteries inside the drone are generally difficult to withstand the working temperature higher than 50 ℃, so that the research on the coating of the drone that can enter a fire scene is slow.

Even so, the existing high temperature resistant coating research reports that the heat insulation mechanism and the corresponding technical scheme still have reference significance. In the aspect of heat insulation, a plurality of technical schemes are that high-porosity fillers (such as hollow microspheres) are added into a coating system ^[8-10] This solution allows the heat to be conducted through the air, thus reducing the thermal conductivity of the coating, but these solutions are generally only suitable for temperature environments below 400 ℃; other schemes are generalThe energy of excessive molecular vibration and rotation continuously makes crystal lattices and bond groups generate collision, and the absorbed heat is re-emitted to the environment, and the material adopted by the proposal is generally silicon carbide ^[11-13] And transition metal oxides (e.g., coO, cuO) ^[14-15] (ii) a There are also solutions to achieve thermal insulation by reflecting radiation, the material chosen being typically TiO2, znO pigments of higher whiteness. Therefore, when the unmanned aerial vehicle coating that can get into the scene of a fire is studied, can refer to above-mentioned heat-insulating mechanism and respective technical scheme and select corresponding material. At the same time, the material chosen is as existing as possible, in view of cost.

In addition to the technical problems and research and development requirements brought by the high-temperature environment, flying chips caused by deflagration often appear in a fire scene, and the flying chips are easy to scratch the coating, so that the high-temperature resistance of the coating is reduced sharply.

In conclusion, the field needs to be studied on the coating of the unmanned aerial vehicle capable of working at the temperature of a fire scene, so that the coating can work in the temperature environment of 1300 ℃ for a long time in the working environment of not higher than 50 ℃ of the unmanned aerial vehicle assembly in the coating, and the coating has certain scratch resistance so as to effectively deal with flying debris in deflagration.

The documents cited in this section are as follows:

[1] liliang, liu is brave, xuqiang, etc. research on thermal injury tests of unmanned aerial vehicles in fire scene environment [ J ]. Reported in Chinese science of safety 31 (2): 7.

[2] Li Miss, liu Xiao Yong, li Liang, etc. research on high and low temperature extreme environment adaptability of lithium ion batteries of unmanned aerial vehicles [ J ]. The science of safety in China, 30 (8): 6.

[3] Wang dod, guanjialin, unmanned aerial vehicle patent technology review [ J ] he south science and technology, 2020,v.39; no.722 (24) 135-138.

[4] The application of unmanned aerial vehicles in the field of forest fire fighting is summarized in J.

[5] Sunji, yangkang, mahong, et al, aviation and aerospace coatings, present status and future development [ J ] Chinese coatings, 2019,034 (001): 28-32.

[6] Qiyuhong, zhangguo beam, xiaunyang, et al, technical progress of thermal insulation coating [ J ] coating industry, 2019,049 (003): 80-87.

[7] Comprehensive, how feared are group rental house fires done to the end? A10 minute surge in room temperature 1300 ℃ [ J ]. Safe and healthy, 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 Gua, preparation of silicon dioxide heat insulation coating and performance characterization [ D ] Harbin industry university.

[10] Xuyongquan, guo xing faithful, hongluying, a heat-insulating coating containing hollow silica microspheres and its application, CN110157315A [ P ].

[11] Wuhaihua, penjianhui, master repent, etc. a graphite/silicon carbide heat-insulating back lining and its preparation method, CN108675790A [ P ].

[12] A composite heat-insulating silicon dioxide coating, CN106082777A [ P ], is prepared from high-strength light, strong dragon, vanli, etc.

[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] Yijianlong, zhanxinming, gurui, etc. the high temperature resistance and corrosion resistance of the cerium oxide-yttrium oxide stabilized zirconia coating on the surface of the magnesium rare earth alloy [ J ] material protection, 2010,43 (8) is 14-16.

Disclosure of Invention

To the not enough and demand that can work unmanned aerial vehicle coating under high temperature environment of prior art, this application aim at provides a high temperature resistant anticorrosion light coating for unmanned aerial vehicle. The unmanned aerial vehicle coating can ensure that the unmanned aerial vehicle assembly in the coating can obtain a working environment not higher than 50 ℃ within 15 minutes at the temperature of 1300 ℃; meanwhile, the coating has the advantages of light weight, corrosion resistance and scratch resistance.

In order to achieve the purpose, the technical scheme adopted by the application is as follows:

the light coating for the high-temperature-resistant anti-corrosion unmanned aerial vehicle comprises 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 a weight ratio of (2-3): (4-6): (7-8): (2-3): (2-3): (1-2).

In the aspect of preparing the heat insulation 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 and heat preservation. Similar materials are expanded polystyrene, aerogel, expanded perlite, and the like. In general, the coating with hollow silica as the main insulation material has a limited insulation effect, and can be used only in low temperature (normal temperature to 200 ℃), and a few coatings based on expanded perlite can be used in medium temperature (200-500 ℃).

Lithium silicate, also called lithium water glass, has better permeability, moldability and heat resistance, and is often used as a raw material in the preparation of heat-insulating coatings ^[16-17] . At present, the temperature resistance of the coating using lithium silicate as a raw material is only a few hundred degrees, no mention that the coating can achieve good heat insulation effect under the environment of thousands of degrees, which is far from the performance of the coating required by the present invention. Yttria is commonly used in aerospace spray-coated insulation materials ^[18-19] Also useful for preparing ablation-resistant coatings ^[20-21] . In the early stage of research, the invention discovers that 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 can be discovered by the heat insulation 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 this finding and has been studied for the preparation of coatings which meet the objects of the present invention.

On the basis, the inventor mixes other common transition metal oxides with the nano yttrium oxide and examines the change of the heat insulation performance of the obtained coating. Unfortunately, no matter 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 research, the inventor finds that after the alpha-phase nano-alumina, the gamma-phase nano-alumina, the nano-magnesia, the nano-zinc borate and the nano-yttrium oxide are mixed, compared with the case of only adding the nano-yttrium oxide, the heat insulation performance of the coating is greatly improved. This suggests that silica hollow microspheres, lithium silicate and the above-mentioned nano-oxide mixture are of crucial importance in the coating system aimed at solving the technical object of the present invention.

We further examine the influence of other system substances and find that the addition of the sulfobetaine can further improve the heat insulation performance of the coating. However, in the system with only nano yttrium oxide, the addition of sulfobetaine has little improvement on the heat insulation performance of the coating. This suggests that the sulfobetaine is likely to provide some dispersion in the mixed nano-oxide system, resulting in more uniform dispersion of the individual nano-oxides in the coating. In addition, in other existing temperature-resistant coatings, the nano oxide is replaced by the nano oxide compound, and the temperature-resistant effect is basically not influenced. This suggests that the use of the role of nano-oxides in radiative heat insulation is likely to be influenced by the interaction of different nano-oxides and may also be limited by the combination of other coating materials. Generally, the hollow microspheres can provide voids for the coating, and the air can form a near vacuum environment under certain conditions to effectively block heat; when the external temperature is too high, the inside of the coating can be deformed, and the deformation is sometimes beneficial to the adhesion of low-melting-point substances and other components, so that the cadmium temperature effect is improved. When the heat insulation and the radiation heat insulation function are in a synergistic effect as a whole, a higher heat insulation effect can be obtained. The silicon dioxide hollow microspheres, the lithium silicate and the selected nano oxide mixture play a remarkable synergistic effect in the aspects of heat insulation and radiation heat insulation.

It is worth pointing out that in the course of the above-mentioned research of the present invention, there is always a focus on solving the problem of scratching caused by deflagration flying debris. The inventors found that the addition of hydroxyethyl methacrylate and nano-alumina silicate fibers is very important.

In the process of research, the inventor of the present invention also considers the corrosion resistance and weight reduction problems of the unmanned aerial vehicle, and based on the above silica hollow microsphere-lithium silicate-nano oxide mixture core component system, the inventor finds that it is also very difficult to obtain the corrosion resistance and the weight reduction. The inventor has additionally applied for a patent on how to have a high temperature and corrosion resistant coating with lighter weight, and details are not described herein.

As a preferable technical scheme of the invention, the component C also comprises 10-15 parts of aqueous polyaspartic acid ester. The preferred technical scheme can obtain higher temperature resistance, and particularly, the maintaining time of the temperature of the base material in the coating layer not higher than 50 ℃ is 17 minutes at 1300 ℃. The film forming matter can form a new active center at the fracture part in a high-temperature environment, further reacts with other components to form a film again, and the temperature resistance is improved. The matching of the waterborne polyaspartic acid ester and the waterborne polyurethane has better effect on re-forming the film and acting with other components.

As a preferable technical scheme of the invention, the nano oxide mixture also comprises nano cerium oxide and nano zinc oxide which are equal to the weight of the nano zinc borate. In this preferred embodiment, the maintenance time can be extended to 18 minutes in the presence of the aqueous polyaspartate.

As an implementable technical scheme of the invention, the particle diameter of each nano oxide in the nano oxide mixture is 100-200 nm.

As a preferable technical scheme of the invention, the grain diameters of the alpha-phase nano-alumina, the gamma-phase nano-alumina and the nano-silica are 100-150 nm, and the grain diameters of the nano-yttrium oxide, the nano-magnesium oxide and the nano-zinc borate are 150-200 nm.

According to the preferable technical scheme, the weight parts of the silica hollow microspheres are 20 parts, the weight parts of the nano oxide mixture are 35 parts, the weight parts of the sulfobetaine are 26 parts, the weight parts of the hydroxyethyl methacrylate are 4 parts, the weight parts of the nano aluminum silicate fibers are 2 parts, and the weight parts of the waterborne polyurethane are 48 parts.

The invention also aims to provide a method for preparing the coating, which is to uniformly mix the components, and add water for stirring during mixing. The method comprises the following steps: mixing the components in the component B according to the parts by weight, adding deionized water, and uniformly stirring at 1000-1500 rpm/min at 50-60 ℃; then adding the component C, stirring at 1000-1500 rpm/min at 70-95 ℃, finally adding the component A, and stirring uniformly at 2000-2500 rpm/min at 50-60 ℃ to obtain the final product.

It is also an object of the present invention to provide the use of the above coating as a coating for a drone. In particular, when the coating is applied, the above excellent high temperature resistance can be obtained only within 0.1mm of the thickness of the coating. As shown in the examples of the present invention, the thickness of the present invention used in the corresponding tests was 0.08mm.

The invention has the beneficial effects that:

the high-temperature-resistant anti-corrosion light coating for the unmanned aerial vehicle has an excellent heat insulation effect, when the thickness of the obtained coating is 0.08mm, the temperature of a coating base material can be not higher than 50 ℃ for more than 15 minutes at 1300 ℃, and meanwhile, the high-temperature-resistant anti-corrosion light coating has good anti-corrosion and anti-scraping functions.

The documents cited in this section:

[16] research on Chenkuxia lithium silicate water-based paint and high-temperature resistant paint [ D ] Nanchang university.

[17] Preparation and performance research of lithium silicate modified water-based polyurethane high-temperature resistant coating [ J ]. Shandong chemical industry, 2019,048 (021): 6-8.

[18] The preparation of NiCr2O4/YSZ composite coating and the heat insulation research thereof [ J ] novel technology and novel process 2018.

[19] Wangle, li Taijiang, li Yong, etc. 45 steel surface atmospheric plasma spraying yttria partially stabilized zirconia thermal barrier coating and its performance [ J ] material protection, 2014 (10).

[20] Yangling, huangzhi, zhang29637, a method for improving the high-temperature resistance and corrosion resistance of thermal barrier coatings, CN112962050A [ P ].

[21] Zhao Yong Traine, zhao, a preparation method of high temperature resistant coating composite material, CN104311146A [ P ].

Drawings

FIG. 1 is a chart of thermograms of the thermal insulation performance test in example 7 of the present invention.

Detailed Description

The present invention is described in detail below by way of examples, and it should be noted that the following examples are only for illustrating the present invention and should not be construed as limiting the scope of the present invention.

In the following experiments, the experimental raw materials and experimental methods used were as follows:

experiment raw materials:

silicon dioxide hollow microspheres: the particle size 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 iron oxide, nanometer copper oxide and nanometer cobalt oxide: purchased from the fertilizer-combination Zhonghang nanotechnology development Co., ltd, the grain diameters of alpha-phase nano-alumina, gamma-phase nano-alumina and nano-silica are 100-150 nm, the grain diameters of the nanometer yttrium oxide, the nanometer magnesium oxide, the nanometer zinc borate, the nanometer iron oxide, the nanometer copper oxide and the nanometer cobalt oxide are 150-200 nm;

lithium silicate, wollastonite powder, kaolin: from Jinan Sheng and chemical Co Ltd

Sulfobetaine, hydroxyethyl methacrylate, polyaspartic acid ester: the laboratory had waterborne polyurethane: prepared from the reference (DOI: 10.19319/j.cnki.issn.1008-021x.2019.21.003)

Surfactant AFCONA-5071: test methods purchased from Shanghai Baiyin chemical Co., ltd:

testing the heat insulation performance: and fixing a blast burner, aligning flame to the center of the sample, vertically burning flame flow onto the sample, and simultaneously testing the back temperature of the tinplate by using an infrared thermometer.

And (3) hardness measurement: the hardness of the coating was determined according to GB/T6739-2006 Pencil test method for coating hardness.

Scratch resistance test: and 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

And (3) placing the sample in a muffle furnace, heating to 1300 ℃ at the temperature of 10 ℃/min, preserving heat for 2h, placing and cooling, and observing and recording whether the coating generates phenomena such as layer opening, peeling, bubbling, cracking and the like after cooling to room temperature (25 ℃). The coated substrate is a ceramic substrate.

The neutral salt spray test was performed: according to GB/T1771-2007, the front and back surfaces of the test plate are sprayed with the coating to be tested, after solidification, paraffin is used for sealing the edge, and the integrity of the coating is observed after the sample lasts for a certain period of time.

Example 1

Preparing the following raw materials in parts by weight:

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 fibers and 48 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 a weight ratio of 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 the same is carried out in other embodiments), and stirring at 1500rpm/min for 30min at 55 ℃; adding sulfobetaine, hydroxyethyl acrylate, nano aluminum silicate fiber and waterborne polyurethane, and stirring at 1500rpm/min at 90 deg.C for 20min; finally, adding the silicon dioxide hollow microspheres and lithium silicate, and stirring at 2500rpm/min for 30min at 55 ℃ to obtain the coating.

Example 2

Preparing the following raw materials in parts by weight:

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 fibers and 40 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 a weight ratio of 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 ℃; adding sulfobetaine, hydroxyethyl acrylate, nano aluminum silicate fiber and waterborne polyurethane, and stirring at 90 deg.C and 1500rpm/min for 20min; finally, adding the silicon dioxide hollow microspheres and lithium silicate, and stirring at 2500rpm/min for 30min at 55 ℃ to obtain the coating.

Example 3

Preparing the following raw materials in parts by weight:

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-alumina silicate fibers 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.

Example 4

Preparing the following raw materials in parts by weight:

20 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 fibers, 40 parts of waterborne polyurethane and 12 parts of waterborne polyaspartic acid ester;

mixing the nano oxide mixture and a surfactant AFCONA-5071, adding deionized water, and stirring at 1500rpm/min for 30min at 55 ℃; adding sulfobetaine, hydroxyethyl acrylate, nano aluminum silicate fiber, waterborne polyurethane and waterborne polyaspartic acid ester, and stirring at 90 ℃ and 1500rpm/min for 20min; finally, adding the silicon dioxide hollow microspheres and lithium silicate, and stirring at 2500rpm/min for 30min at 55 ℃ to obtain the coating.

Example 5

The weight parts of the aqueous polyaspartic acid ester are 10 parts compared to example 4, and the rest is the same as example 4.

Example 6

The weight parts of the aqueous polyaspartic ester compared to example 4 were 15 parts, the remainder being identical to example 4.

Example 7

Preparing the following raw materials in parts by weight:

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 in a weight ratio of 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 ℃; adding sulfobetaine, hydroxyethyl methacrylate, nano aluminum silicate fiber, waterborne polyurethane and waterborne polyaspartic acid ester, and stirring at 90 ℃ at 1500rpm/min for 20min; finally, adding the silicon dioxide hollow microspheres and lithium silicate, and stirring at 2500rpm/min for 30min at 55 ℃ to obtain the coating.

The above examples 1-7 were tested and the results are shown in table 1:

TABLE 1

Note 1: in Table 1, in the test of the heat insulating property, the outer flame temperature was 1300 to 1350 ℃, the thickness of the coating was 0.08mm, and the substrate was a tinplate (thickness: 4.6 mm). The temperature off time is the time that the temperature of the back of the tinplate is maintained below 50 ℃ under the flame alignment coating spray.

Note 2: in table 1, "appearance after ablation" reflects the heat resistance test result, and smoothness means that no phenomena such as delamination, peeling, bubbling, and cracking occur, and the coating is in a smooth state.

The temperature change during the experiment of example 7 was recorded in this experiment. As shown in figure 1, the temperature rises steadily and slightly in the stage of 0-4.5 minutes, and rises greatly (from 29.4 ℃ to 34.6 ℃) in the stage of 4.5-5.5 minutes; after that, in the 5.5-9 minute period, a temperature rising period with a slightly larger amplitude but a smooth trend (from 34.6 ℃ to 41.3 ℃) is presented; then, in the 9-18 minute period, a steady small rising trend (rising from 41.3 ℃ to 49.8 ℃) is presented; finally, in the stage of 18-20.5 minutes, the temperature is rapidly increased from 49.8 ℃ to 100 ℃ within 2 minutes.

Comparative example 1

Before the invention obtains the technical schemes of the embodiments 1-7, other technical schemes are considered, and the representative technical scheme is as follows:

technical scheme 1-1:

preparing the following raw materials in parts by weight:

20 parts of silicon dioxide 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 uniformly (500 rpm/min) to obtain the final product.

Technical means 1 to 2

20 parts of silicon dioxide hollow microspheres, 35 parts of lithium silicate, 1 part of surfactant AFCONA-5071, 20 parts of kaolin and 40 parts of waterborne polyurethane;

Technical schemes 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;

Technical scheme 2-1

20 parts of silicon dioxide 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 uniformly (500 rpm/min) to obtain the final product. The nano-oxide mixture is prepared by mixing alpha-phase nano-alumina, gamma-phase nano-alumina, nano-magnesia, nano-zinc borate and nano-yttrium oxide according to the weight ratio of 1.

Technical solution 2-2

20 parts of silicon dioxide 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 uniformly (500 rpm/min) to obtain the final product. The nano-oxide mixture is prepared by mixing alpha-phase nano-alumina, gamma-phase nano-alumina, nano-magnesium oxide, nano-zinc borate and nano-yttrium oxide according to the weight ratio of 1.

The technical scheme is subjected to heat insulation performance test, the outer flame temperature is 400-420 ℃, the coating thickness is 0.1mm, the substrate is a tinplate (thickness is 4.6 mm), and the results are shown in Table 2.

TABLE 2

Note: in Table 2, the soak time is the time during which the temperature of the back of the tin plate is maintained below 50 ℃ under the flame-aligned coating spray.

Comparative example 2

Technical solution 3-1

Referring to 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.

Technical solution 3-2

Referring to 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.

Technical means 3 to 3

Referring to 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.

Technical schemes 3 to 4

On the basis of the technical scheme 1-3, 20 parts of sulfobetaine are added.

According to the test method of the heat insulating property of comparative example 1, the heat insulating time did not exceed 350 seconds.

Claims

1. The high-temperature-resistant anti-corrosion 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 portion of the material is as follows:

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 a weight ratio of (2-3): (4-6): (7-8): (2-3): (2-3): (1-2).

2. The lightweight coating according to claim 1, wherein the nano-oxide mixture comprises nano-oxides each having a particle size of 100 to 200nm; the particle size of the silicon dioxide hollow microsphere is 200-300 nm.

3. The lightweight coating of claim 2, wherein the alpha phase nano alumina, gamma phase nano alumina and nano silica have a particle size of 100-150 nm, and the nano yttria, magnesia and zinc borate have a particle size of 150-200 nm.

4. The lightweight coating of claim 1, further comprising 10 to 15 parts of an aqueous polyaspartic acid ester in component C.

5. The lightweight coating of claim 4, wherein said nano-oxide mixture further comprises nano-cerium oxide and nano-zinc oxide in an amount equal in weight to nano-zinc borate.

6. 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.

7. the lightweight coating according to 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-alumina silicate fibers are 2 parts by weight, and the aqueous polyurethane is 48 parts by weight.

8. A preparation method of a high-temperature-resistant anti-corrosion light-weight coating is characterized in that the high-temperature-resistant anti-corrosion light-weight coating is the high-temperature-resistant anti-corrosion light-weight coating according to any one of claims 1 to 7, and the preparation method comprises the steps of uniformly mixing the components, adding water and stirring during mixing.

9. The preparation method of claim 8, 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 uniformly stirred at 1000-1500 rpm/min at 50-60 ℃; then adding the component C, stirring at 1000-1500 rpm/min at 70-95 ℃, finally adding the component A, and stirring uniformly at 2000-2500 rpm/min at 50-60 ℃ to obtain the final product.

10. Use of the high temperature resistant anti-corrosion lightweight coating according to any of claims 1 to 8 or produced by the production method according to claim 8 or 9 as a coating for unmanned aerial vehicles, characterized in that the thickness of the coating does not exceed 0.1mm.