CN109021785A - A kind of efficient solar heat protection heat-proof coating material and its manufacturing method - Google Patents
A kind of efficient solar heat protection heat-proof coating material and its manufacturing method Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D163/00—Coating compositions based on epoxy resins; Coating compositions based on derivatives of epoxy resins
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08G—MACROMOLECULAR COMPOUNDS OBTAINED OTHERWISE THAN BY REACTIONS ONLY INVOLVING UNSATURATED CARBON-TO-CARBON BONDS
- C08G59/00—Polycondensates containing more than one epoxy group per molecule; Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups
- C08G59/18—Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups ; e.g. general methods of curing
- C08G59/40—Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups ; e.g. general methods of curing characterised by the curing agents used
- C08G59/44—Amides
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- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
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Abstract
The present invention provides a kind of efficient solar heat protection heat-proof coating material and its manufacturing methods, are uniformly mixed after 650 Versamids, 651 Versamids, 2-ethyl-4-methylimidazole are weighed；The diluent of X-12 solvent, ethyl acetate and dehydrated alcohol composition is added, is thoroughly mixed, is configured to 50% Versamid composite curing agent system, forms B component；Glass microballoon, iron oxide, mica powder, polyphosphoric acid amine, aluminium hydroxide, silica and silicon carbide are dried into 5h in 80 DEG C of drying box, natural cooling obtains component C；Component C is sufficiently stirred with B component and 100 mass parts ES-06 epoxy silicone resins when use.The present invention has the characteristics that low-density, ablation resistance be good, not swelling and cracking after curing of coatings, high comprehensive performance.
Description
Technical field
The present invention relates to a kind of low-density, solar heat protection is heat-insulated, the washcoat of resistance to ablation and preparation method thereof, is applied to high horse
The solid propellant rocket outer heat shield of conspicuous number flight.
Background technique
With the development of modern space flight and aviation technology, aircraft (solid-rocket) long-time in atmosphere with High Mach number
Flight, due to Aerodynamic Heating, if outer heat shield is taken effective measures, not only instrument be can not work normally in internal weapon bays, but also metal
The monomer structure of material also unbearable thermal force high in this way.To guarantee that aircraft is flown safely in atmosphere with High Mach number
Row is it is necessary to aircraft outer surface progress thermal protection.Thermally protective materials will have preferable heat-proof quality, good resistance to erosion
Performance, higher mechanical property and lower density.
According to aircraft exterior thermally protective materials use condition and function difference, can be divided at present resin base, it is carbon-based,
The composite materials such as ceramic base and solar heat protection heat-proof coating material.Common thermally protective materials can be divided into distillation by working mechanism again
Type, fusing type, breakdown type, carbonization type and compound, take away a large amount of heat by the consumption of material surface quality, reach prevention heat
Spread the purpose into material internal.But for mechanism, most of thermally protective materials belong to compound.Their most important function
It can be in several Baidu, the high temperature of thousands of degree and under washing away, heat insulation material gradually " melts ", reaches to aircraft and its emitter
Play the role of thermal protection.Thermal protective coating is not limited, therefore application range because its craftsmanship is good by product surface shape
Extensively.
The heat-insulated washcoat of resistance to ablation of low-density solar heat protection (abbreviation thermal protective coating) research is related to space technology, material power
, hydrodynamics, thermodynamics, chemical kinetics, high molecular material and the technologies such as special detection and test.Thermal protective coating master
It will be by groups such as polymer (resin) matrix, fire retardant, curing agent, reinforcing filler, heat-barrier material, heat insulation material and other auxiliary agents
At.Process common are spraying, blade coating, brushing etc., the curing molding under certain temperature and time, to aircraft itself
Play that solar heat protection is heat-insulated and heat resistanceheat resistant stream denudation.The thickness of general common coating (including paint) is within 0.2mm, but solar heat protection is heat-insulated
Coating is according to the difference of aircraft flight condition, and thermal protective coating thickness is in 0.2mm~4mm range.In view of thermal protective coating is subsequent
Polishing, turning etc. are needed in technique, practical coating thickness is bigger, and this requires thermal protective coatings in addition to functional attributes, craftsmanship
It is higher than common coating.
At the beginning of the technology of the present invention research, the related data of domestic and international thermal protective coating is retrieved, there is Beijing Aviation space flight
The basic research project " low bulk density thermal insulating filling and efficient low-density ablation surface " of university, the coating density being related to is low, intensity
Small, technique is not studied, and belongs to general research work.Two kinds of serial thermal protective coatings that the space flight Ke Gong forth academy develops, have been answered
With on certain aircraft.By test and actual tests, a kind of coating ablation resistance is poor, and oxy-acetylene linear ablative rate is greater than
0.45mm/s, paint solidification temperature are more than 120 DEG C, and coating is more crisp, are easy swelling and cracking.Another coating, little sample testing is intact,
But when being applied to practical flight device hot test, coating is more crisp and de- to be split.Both families of coatings are not able to satisfy novel flight
The anti-heat request of device.The serial thermal protective coating product that Chinese coating research institute develops, also has been applied to certain aircraft exteriors
In solar heat protection, by trying mapping, thermal insulation is poor, and thermal coefficient is more than 0.45W/ (mk), and shrinking percentage is big when solidification, and coating adds
It is thick just to crack, it is not suitable with the anti-heat request of high-speed aircraft.The countries such as the U.S., the former Soviet Union, thermal protective coating application is more early, but specific
Coating is prepared and preparation method open source information is less (including patent).
Currently, the flying speed of aircraft is getting faster (3~5 Mach), the flight time is increasingly longer, to its external solar heat protection
Requirement it is more and more harsher, should resistance to ablation, antiscour, solar heat protection, heat insulation are good again, in addition, the density of coating want it is low,
The adhesive force having had is unable to unsticking, cracking and bulge, also to have good toughness and spraying process.In addition, coating is high
Temperature solidifies the safety limitation for being subject to aircraft (solid propellant rocket) under charge constitution.Meanwhile coating process
It can need just to be able to verify that by scale-up, small-scale test effect is fine, but can not be applied to actual product after amplifying, the reason is that
Not only mutually collaboration mutually restricts again between the main performance of thermal protective coating, resistance to ablation and heat-insulated, antiscour and low-density, it is heat-resisting and
Toughness, high-intensitive and crackle, coating layer thickness and craftsmanship etc., therefore, the external solar heat protection heat insulating coat research of course of new aircraft is
Pursue a kind of satisfaction of comprehensive performance, emphasis solve poor existing coating high-temp solidification, ablation resistance, cure shrinkage, toughness compared with
Difference, the problems such as swelling and cracking and spraying process are poor.
Summary of the invention
For overcome the deficiencies in the prior art, the present invention provides that a kind of low-density, efficient solar heat protection be heat-insulated, intermediate temperature setting, spray
The coating for applying good manufacturability is related to matrix resin screening, the suitability optimization of intermediate temperature setting system, function of solar heat protection heat insulating coat
The selection of filler and dosage optimization, the compatibility and craftsmanship verification test of diluent, the performance test of coating and preparation and
Sprayability engineer testing, be able to solve High Mach number, long endurance flight aircraft outer solar heat protection the problem of, focus on solving existing
After the thermal insulation of coating is poor, brittleness is high, hot setting limits to and solidification the problems such as bulge crackle.
The technical solution adopted by the present invention to solve the technical problems is: a kind of efficient solar heat protection heat-proof coating material, group
Divide includes 100 mass parts ES-06 epoxy silicone resins, 10~20 mass parts, 650 Versamid, 4~8 mass parts 651
Versamid, 2~4 mass parts 2-ethyl-4-methylimidazoles, 6~15 mass parts glass microballoons, the oxidation of 3~6 mass parts
Iron, 18~30 mass parts mica powders, 6~12 mass parts polyphosphoric acid amines, 8~16 mass parts aluminium hydroxides, 10~20 mass parts two
Silica and 6~12 mass parts silicon carbide.
The glass microballoon and silicon carbide is 1000 mesh materials, and mica powder is 200 mesh materials, aluminium hydroxide and titanium dioxide
Silicon is 120 mesh materials；Iron oxide and polyphosphoric acid amine are technical grade material.
The present invention also provides the manufacturing methods of above-mentioned efficient solar heat protection heat-proof coating material, comprising the following steps: by 650 low points
Sub- polyamide, 651 Versamids, 2-ethyl-4-methylimidazole are uniformly mixed after weighing by above-mentioned proportion by weight；It is added
The diluent of X-12 solvent, ethyl acetate and dehydrated alcohol composition, is thoroughly mixed, is configured to 50% Versamid
Composite curing agent system forms B component；The mass ratio of the X-12 solvent, ethyl acetate and dehydrated alcohol is 5:2:1；It will
Glass microballoon, iron oxide, mica powder, polyphosphoric acid amine, aluminium hydroxide, silica and silicon carbide dry in 80 DEG C of drying box
Dry 5h, natural cooling obtain component C；Component C and B component and 100 mass parts ES-06 epoxy silicone resins are abundant when use
Stirring.
The beneficial effects of the present invention are: the external solar heat protection of the course of new aircraft for the long endurance flight of High Mach number, first
Solar heat protection insulating mechanism is had studied, by the compounding and modification of basic resin system, the screening of curing system and compound, functional stuffing
Selection and optimization, unique innovation of preparation process, test examination, develops the new coating of high comprehensive performance comprehensively, solves
The anti-heat problem in outside of the long endurance aircraft of High Mach number of having determined.
Situations such as present invention starts with from research heat insulation material mechanism, external heating when comprehensive consideration of flight vehicle flight, adopts
With preferred, type selecting and compound, positioning room temperature, intermediate temperature setting of the curing system using several components of several resin matrixes.Function
Filler uses thermal-insulating system, solar heat protection system, flame-retardant system, and the optimum proportioning of functional stuffing component has been determined by Orthogonal Method.This
Thermal protective coating, preparation process and the Performance Testing verification method of invention, it is special by the country of the internet to State Intellectual Property Office
The inquiry of benefit and the foreign patent mechanism of link, the thermal protective coating correlation for not finding comprehensive performance better than the invention patent are believed
Breath.
The thermal protective coating developed of the present invention, not only meeting the anti-heat demand in outside of course of new aircraft, (flight test is tested
Card), also there is intermediate temperature setting (aircraft powder charge state can only low temperature or intermediate temperature setting for security consideration) characteristic, have
Low-density, ablation resistance be good, after curing of coatings not swelling and cracking (good toughness) the features such as, high comprehensive performance.Also succeed simultaneously
Using the outer solar heat protection of Mr. Yu's attitude control engine cabin.
Specific embodiment
Below with reference to embodiment, the present invention is further described, and the invention includes, but is not limited to, the following examples.
The technical solution adopted by the present invention is that: the heat-insulated resistance to ablation resistance to erosion flexible coating of low-density solar heat protection, intermediate temperature setting, packet
Include coated substrate resin (component A), curing system (B component), functional stuffing system (C component), constituent and each ingredient
Mass fraction proportion it is as shown in table 1.
1 low-density solar heat protection heat insulating coat basic recipe of table
In table 1, the main function of component A heat resist modification organic siliconresin is film forming and enhances heat resistance, there are commonly
Machine resin has alkyd resin, polyester resin, acrylic resin, phenolic resin and epoxy resin etc., and the present invention uses ES-06 epoxy
Organic siliconresin, gel content 50%, epoxide number 0.086, viscosity are about 30~40S (applying 4 glasss).
B component is curative systems, since Coating base of the invention uses epoxy silicone resin, selects different consolidate
Agent can solidify at different temperature, in conjunction with security requiremenies such as aircraft product powder charges, it is desirable that room temperature or intermediate temperature setting,
So the present invention selects Versamid and imidazoles composite curing agent, 45 DEG C/48h that can be fully cured, coating is tough after solidification
Property is good.
C component is functional filler, and table 1 shows that each component each serves as solar heat protection, heat-insulated and fire retardation.
Efficient solar heat protection heat insulating coat preparation method of the present invention:
(1) prepared by component A
The present invention considers it is to set thermal protective coating to two components of A, B at first, i.e., component A is that matrix resin+function is filled out
Material, B component is curative systems.But when coating, which mixes, to be stored for a long time, the functional stuffing in component A sinks in matrix resin
Product agglomeration, when use, are difficult to be uniformly mixed, then individually list the functional stuffing in component A, it is determined as C component.So component A is
Single ES-06 epoxy silicone resin, and facilitate production and packaging.
(2) B component prepares (curing system)
By 650 Versamids, 651 Versamids, 2-ethyl-4-methylimidazole by table 1 proportion weigh after according to
Secondary addition has in the mixing vessel of blender (agitator air), starts blender and is pre-mixed uniformly.1 ratio of table is pressed again
X-12, ethyl acetate and dehydrated alcohol equal solvent is added, is thoroughly mixed 30min, is configured to 50% Versamid
Composite curing agent system forms B component.
(3) C component prepares (functional stuffing)
The C component of efficient solar heat protection heat insulating coat of the present invention be mixed fillers, be followed successively by glass microballoon, iron oxide,
The specification of mica powder, polyphosphoric acid amine, aluminium hydroxide, silica and silicon carbide, each component is shown in Table 1.
Firstly, before C component mixed preparing, by glass microballoon, iron oxide, mica powder, polyphosphoric acid amine, aluminium hydroxide, two
Silica and silicon carbide successively dry 5h in 80 DEG C of dry picture, pack and are sealed after natural cooling.
Secondly, the various fillers of C component are sequentially added in mixer by the proportion of table 1, starts blender and be sufficiently stirred
30min or more is packed into packing tube, seals storage.
Efficient solar heat protection heat insulating coat curing cycle of the present invention are as follows:
1) (general 20 DEG C) can be fully cured for 7 days under room temperature, be suitable for coating layer thickness in 0.5mm or less；
2) 45 DEG C/48h solidifies, and is suitable for the lesser curing of coatings of thickness, generally in 1mm or less；
3) cured in stages of 45 DEG C of -60 DEG C of ranges is suitable for the biggish curing of coatings of thickness, generally in 1mm or more.
The explanation for the coating special diluting agent that 5.3 present invention develop
The present invention is that coating spraying technical process has developed special diluting agent, i.e., by X-12 solvent, ethyl acetate and anhydrous
Ethyl alcohol is added in mixer by quality proportioning 5:2:1, and pneumatic stirring is uniformly mixed, and is configured to special diluting agent.
Special diluting agent is mainly used in coating spraying technical process, can be appropriate according to the requirement of user's spraying process
It adds or is not added, viscosity when for adjusting coating spraying, diluent is not participated in coating itself and chemically reacted, to coating property
It does not influence, dosage does not account for formulation dosage.
Test effect of the present invention such as table 2.
2 the performance test results of table and testing standard
Firstly, being described further to raw material sources of the present invention.
The source for each component that embodiment of the present invention uses:
1.ES-06 epoxy silicone resin, Jiangsu Wujiang resultant force resin processing plant；
2.650 Versamids, 651 Versamids, the Xiangtan City chemical plant Zhao Tan
3.2- ethyl -4-methylimidazole, Tianjin chemical reagent factory；
4. iron oxide, Shanghai Iron Oxide Pigment Factory；
5. glass microballoon, Shanghai Ge Run sub-nanometer Materials Co., Ltd；
6. silica, Spring in Pig House of Shanghai Fengxian chemical reagent work；
7. mica, Shanghai Jinshan Lv Xiang mica powder factory；
8. ammonium polyphosphate, Zhejiang chemical science and technology group company；
9. silicon carbide, Zhengzhou City Dong Sheng diamond dust Chang Shuanli silicon carbide articles Co., Ltd；
10. aluminium hydroxide, Shanghai Ge Run sub-nanometer Materials Co., Ltd；
11.X-12 diluent, Xi'an Li'ao Technology Co., Ltd.；
12. ethyl acetate, Xi'an chemical reagent factory；
13. dehydrated alcohol, Xi'an chemical reagent factory.
Embodiment 1
Implement product: I type High Mach number aircraft exterior solar heat protection, coating thickness requirement 0.45mm~0.65mm, painting used
Layer formula is shown in Table 3.
3 low-density solar heat protection heat insulating coat formula composition of table
| Serial number | Ingredient | It matches (mass parts) | Effect |
| 1 | ES-06 epoxy silicone resin | 100 | Film forming |
| 2 | 650 Versamids | 10 | Tough curing agent |
| 3 | 651 Versamids | 4 | Tough curing agent |
| 4 | 2-ethyl-4-methylimidazole | 2 | Curing agent |
| 5 | Glass microballoon (1000 mesh) | 6 | It is heat-insulated |
| 6 | Iron oxide (industry) | 3 | Solar heat protection |
| 7 | Mica powder (200 mesh) | 18 | It is heat-insulated |
| 8 | Polyphosphoric acid amine (industry) | 6 | It is fire-retardant |
| 9 | Aluminium hydroxide (120 mesh) | 8 | It is fire-retardant |
| 10 | Silica (120 mesh) | 10 | Solar heat protection |
| 11 | Silicon carbide (1000 mesh) | 6 | Solar heat protection, carbon sequestration |
| 12 | Special diluting agent | 5 | Craftsmanship diluent |
Coating preparation and spraying process method: it according to I type High Mach number aircraft outer dimension and coating thickness requirement, applies
Material is prepared by 5.1 method above, and special diluting agent dosage is 5 parts of mass parts.Spraying parameter setting are as follows: spray pressure
0.4MPa~0.6MPa, 30 DEG C ± 5 DEG C of environment temperature, each (layer) sprayed coating thickness 0.15mm ± 0.05mm, every layer of spraying
Interval time is 40min ± 5min, until spraying to design predetermined thickness.
This formula thermal protective coating curing cycle: product is placed into drying box, and 45 DEG C of solidification temperature, curing time 48h.
Performance and it the results are shown in Table 4.
4 performance of table and its test result
Embodiment 2
Implement product: the novel long endurance aircraft exterior solar heat protection of II type, coating spraying thickness 4.5mm~5.5mm, turning are arrived
3.5mm ± 0.1mm, used coating formula are shown in Table 5.
5 low-density solar heat protection heat insulating coat formula composition of table
| Serial number | Component | It matches (mass parts) | Effect |
| 1 | ES-06 epoxy silicone resin | 100 | Film forming |
| 2 | 650 Versamids | 20 | Tough curing agent |
| 3 | 651 Versamids | 8 | Tough curing agent |
| 4 | 2-ethyl-4-methylimidazole | 4 | Curing agent |
| 5 | Glass microballoon (1000 mesh) | 15 | It is heat-insulated |
| 6 | Iron oxide (industry) | 6 | Solar heat protection |
| 7 | Mica powder (200 mesh) | 25 | It is heat-insulated |
| 8 | Polyphosphoric acid amine (industry) | 10 | It is fire-retardant |
| 9 | Aluminium hydroxide (120 mesh) | 14 | It is fire-retardant |
| 10 | Silica (120 mesh) | 20 | Solar heat protection |
| 11 | Silicon carbide (1000 mesh) | 10 | Solar heat protection, carbon sequestration |
| 12 | Special diluting agent | 0 | Craftsmanship diluent |
Coating preparation and spraying process method: it is wanted according to the novel long endurance aircraft outer dimension of II type and coating layer thickness
It asks, coating is prepared by 5.1 method above, good to meet coating spraying since this product thermal protective coating thickness requirement is thicker
Craftsmanship avoids coating sagging in spraying process, special diluting agent is not added in this formula.Spraying parameter setting are as follows: spray
Apply pressure 0.35MPa~0.45MPa, 30 DEG C ± 5 DEG C of environment temperature, each (layer) sprayed coating thickness 0.10mm ± 0.05mm,
Every layer of spraying interval time 30min ± 5min, until spraying to design predetermined thickness.
This formula heat-resistant paint curing cycle: I stage: temperature 45 C/48h；II stage: temperature 60 C/20h.
Performance and it the results are shown in Table 6.
6 performance of table and its test result
Embodiment 3
III type vehicle launch equips internal solar heat protection, coating layer thickness 0.15mm~0.25mm, and used coating formula is shown in Table 7.
7 low-density solar heat protection heat insulating coat formula composition of table
| Serial number | Component | It matches (mass parts) | Effect |
| 1 | ES-06 epoxy silicone resin | 100 | Film forming |
| 2 | 650 Versamids | 15 | Tough curing agent |
| 3 | 651 Versamids | 8 | Tough curing agent |
| 4 | 2-ethyl-4-methylimidazole | 3 | Curing agent |
| 5 | Glass microballoon (1000 mesh) | 13 | It is heat-insulated |
| 6 | Iron oxide (industry) | 5 | Solar heat protection |
| 7 | Mica powder (200 mesh) | 23 | It is heat-insulated |
| 8 | Polyphosphoric acid amine (industry) | 8 | It is fire-retardant |
| 9 | Aluminium hydroxide (120 mesh) | 12 | It is fire-retardant |
| 10 | Silica (120 mesh) | 15 | Solar heat protection |
| 11 | Silicon carbide (1000 mesh) | 9 | Solar heat protection, carbon sequestration |
| 12 | Special diluting agent | 0 | Craftsmanship diluent |
Coating preparation and spraying process method: solar heat protection and coating thickness requirement, coating are equipped according to III type vehicle launch
It is prepared by 5.1 method above, since this product thermal protective coating thickness requirement is relatively thin, sprays good craftsmanship to meet coating,
Coating sagging is avoided in spraying process, and special diluting agent is not added in this formula.Spraying parameter setting are as follows: spray pressure
0.30MPa~0.35MPa, under environment temperature room temperature (20 DEG C ± 5 DEG C), each (layer) sprayed coating thickness 0.10mm ±
0.05mm, every layer of spraying interval time 4h, spraying twice is i.e. to design predetermined thickness.
This formula thermal protective coating curing cycle: (20 DEG C ± 5 DEG C), curing time 48h under room temperature.
Performance and it the results are shown in Table 8.
8 performance of table and its test result
Claims (3)
1. a kind of efficient solar heat protection heat-proof coating material, it is characterised in that: its component includes 100 mass parts ES-06 epoxy organosilicons
Resin, 10~20 mass parts, 650 Versamid, 4~8 mass parts, 651 Versamid, 2~4 mass parts 2- ethyls-
4-methylimidazole, 6~15 mass parts glass microballoons, 3~6 mass parts iron oxide, 18~30 mass parts mica powders, 6~12 mass
Part polyphosphoric acid amine, 8~16 mass parts aluminium hydroxides, 10~20 mass parts silica and 6~12 mass parts silicon carbide.
2. efficient solar heat protection heat-proof coating material according to claim 1, it is characterised in that: the glass microballoon and carbonization
Silicon is 1000 mesh materials, and mica powder is 200 mesh materials, and aluminium hydroxide and silica are 120 mesh materials；Iron oxide and polyphosphoric acid
Amine is technical grade material.
3. the preparation method of efficient solar heat protection heat-proof coating material described in a kind of claim 1, it is characterised in that include the following steps:
It is mixed after 650 Versamids, 651 Versamids, 2-ethyl-4-methylimidazole are weighed by above-mentioned proportion by weight
Uniformly；Be added X-12 solvent, ethyl acetate and dehydrated alcohol composition diluent, be thoroughly mixed, be configured to 50% it is low
Molecular polyamide composite curing agent system forms B component；The mass ratio of the X-12 solvent, ethyl acetate and dehydrated alcohol
For 5:2:1；By glass microballoon, iron oxide, mica powder, polyphosphoric acid amine, aluminium hydroxide, silica and silicon carbide at 80 DEG C
5h is dried in drying box, natural cooling obtains component C；Component C and B component and 100 mass parts ES-06 epoxies are organic when use
Silicone resin is sufficiently stirred.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111019424A (en) * | 2019-12-04 | 2020-04-17 | 北京科技大学 | Vacuum ceramic microbead heat-insulating anticorrosive paint for steel structure equipment and preparation method thereof |
| CN112480789A (en) * | 2020-11-15 | 2021-03-12 | 西安长峰机电研究所 | High-strength anti-scouring ablation-resistant heat-proof coating material and preparation method thereof |
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| CN111019424B (en) * | 2019-12-04 | 2021-07-23 | 北京科技大学 | Vacuum ceramic microbead heat-insulating anticorrosive paint for steel structure equipment and preparation method thereof |
| CN112480789A (en) * | 2020-11-15 | 2021-03-12 | 西安长峰机电研究所 | High-strength anti-scouring ablation-resistant heat-proof coating material and preparation method thereof |
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Application publication date: 20181218 |