CN116396628A - High-temperature-resistant protective coating repairing material and online repairing method - Google Patents
High-temperature-resistant protective coating repairing material and online repairing method Download PDFInfo
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- CN116396628A CN116396628A CN202111612006.0A CN202111612006A CN116396628A CN 116396628 A CN116396628 A CN 116396628A CN 202111612006 A CN202111612006 A CN 202111612006A CN 116396628 A CN116396628 A CN 116396628A
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- coating
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- filler
- repair
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- 239000000463 material Substances 0.000 title claims abstract description 97
- 238000000034 method Methods 0.000 title claims abstract description 25
- 239000011253 protective coating Substances 0.000 title claims abstract description 14
- 238000000576 coating method Methods 0.000 claims abstract description 134
- 239000011248 coating agent Substances 0.000 claims abstract description 132
- 230000008439 repair process Effects 0.000 claims abstract description 81
- 239000000843 powder Substances 0.000 claims abstract description 68
- 239000000945 filler Substances 0.000 claims abstract description 58
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 45
- 229910052751 metal Inorganic materials 0.000 claims abstract description 42
- 239000002184 metal Substances 0.000 claims abstract description 42
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 41
- 230000005855 radiation Effects 0.000 claims abstract description 39
- 239000011230 binding agent Substances 0.000 claims abstract description 37
- 239000003085 diluting agent Substances 0.000 claims abstract description 37
- 239000011159 matrix material Substances 0.000 claims abstract description 32
- 239000000080 wetting agent Substances 0.000 claims abstract description 27
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims abstract description 26
- GFQYVLUOOAAOGM-UHFFFAOYSA-N zirconium(iv) silicate Chemical compound [Zr+4].[O-][Si]([O-])([O-])[O-] GFQYVLUOOAAOGM-UHFFFAOYSA-N 0.000 claims abstract description 22
- 229910052582 BN Inorganic materials 0.000 claims abstract description 21
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 21
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims abstract description 21
- 229910052581 Si3N4 Inorganic materials 0.000 claims abstract description 21
- CNLWCVNCHLKFHK-UHFFFAOYSA-N aluminum;lithium;dioxido(oxo)silane Chemical compound [Li+].[Al+3].[O-][Si]([O-])=O.[O-][Si]([O-])=O CNLWCVNCHLKFHK-UHFFFAOYSA-N 0.000 claims abstract description 21
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 claims abstract description 21
- 239000011863 silicon-based powder Substances 0.000 claims abstract description 21
- 229910052644 β-spodumene Inorganic materials 0.000 claims abstract description 21
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 20
- 239000010703 silicon Substances 0.000 claims abstract description 20
- 239000004111 Potassium silicate Substances 0.000 claims abstract description 16
- 229910052913 potassium silicate Inorganic materials 0.000 claims abstract description 16
- NNHHDJVEYQHLHG-UHFFFAOYSA-N potassium silicate Chemical compound [K+].[K+].[O-][Si]([O-])=O NNHHDJVEYQHLHG-UHFFFAOYSA-N 0.000 claims abstract description 16
- 235000019353 potassium silicate Nutrition 0.000 claims abstract description 16
- 239000004115 Sodium Silicate Substances 0.000 claims abstract description 15
- 229910052911 sodium silicate Inorganic materials 0.000 claims abstract description 15
- NTHWMYGWWRZVTN-UHFFFAOYSA-N sodium silicate Chemical compound [Na+].[Na+].[O-][Si]([O-])=O NTHWMYGWWRZVTN-UHFFFAOYSA-N 0.000 claims abstract description 15
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 34
- YXFVVABEGXRONW-UHFFFAOYSA-N Toluene Chemical compound CC1=CC=CC=C1 YXFVVABEGXRONW-UHFFFAOYSA-N 0.000 claims description 24
- 238000002156 mixing Methods 0.000 claims description 20
- KFZMGEQAYNKOFK-UHFFFAOYSA-N Isopropanol Chemical compound CC(C)O KFZMGEQAYNKOFK-UHFFFAOYSA-N 0.000 claims description 18
- 229920005989 resin Polymers 0.000 claims description 18
- 239000011347 resin Substances 0.000 claims description 18
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 16
- LRHPLDYGYMQRHN-UHFFFAOYSA-N N-Butanol Chemical compound CCCCO LRHPLDYGYMQRHN-UHFFFAOYSA-N 0.000 claims description 16
- 239000000835 fiber Substances 0.000 claims description 16
- DNIAPMSPPWPWGF-UHFFFAOYSA-N Propylene glycol Chemical compound CC(O)CO DNIAPMSPPWPWGF-UHFFFAOYSA-N 0.000 claims description 15
- 239000002002 slurry Substances 0.000 claims description 15
- 239000003054 catalyst Substances 0.000 claims description 12
- 238000005507 spraying Methods 0.000 claims description 12
- 239000000377 silicon dioxide Substances 0.000 claims description 11
- 239000002904 solvent Substances 0.000 claims description 11
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 10
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 9
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 claims description 9
- 229920000647 polyepoxide Polymers 0.000 claims description 7
- 239000004964 aerogel Substances 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 6
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims description 6
- 239000008367 deionised water Substances 0.000 claims description 5
- 229910021641 deionized water Inorganic materials 0.000 claims description 5
- 229940113115 polyethylene glycol 200 Drugs 0.000 claims description 5
- 235000011187 glycerol Nutrition 0.000 claims description 4
- 238000009413 insulation Methods 0.000 claims description 4
- 238000005303 weighing Methods 0.000 claims description 3
- 229920002050 silicone resin Polymers 0.000 claims description 2
- 239000004593 Epoxy Substances 0.000 claims 1
- 238000000227 grinding Methods 0.000 description 16
- YGSDEFSMJLZEOE-UHFFFAOYSA-N salicylic acid Chemical compound OC(=O)C1=CC=CC=C1O YGSDEFSMJLZEOE-UHFFFAOYSA-N 0.000 description 10
- WGTYBPLFGIVFAS-UHFFFAOYSA-M tetramethylammonium hydroxide Chemical compound [OH-].C[N+](C)(C)C WGTYBPLFGIVFAS-UHFFFAOYSA-M 0.000 description 10
- 229910000428 cobalt oxide Inorganic materials 0.000 description 9
- IVMYJDGYRUAWML-UHFFFAOYSA-N cobalt(ii) oxide Chemical compound [Co]=O IVMYJDGYRUAWML-UHFFFAOYSA-N 0.000 description 9
- 230000006378 damage Effects 0.000 description 9
- 238000005498 polishing Methods 0.000 description 9
- 239000010453 quartz Substances 0.000 description 9
- 244000137852 Petrea volubilis Species 0.000 description 8
- 238000007873 sieving Methods 0.000 description 8
- 238000005336 cracking Methods 0.000 description 7
- YXTPWUNVHCYOSP-UHFFFAOYSA-N bis($l^{2}-silanylidene)molybdenum Chemical compound [Si]=[Mo]=[Si] YXTPWUNVHCYOSP-UHFFFAOYSA-N 0.000 description 6
- MANYRMJQFFSZKJ-UHFFFAOYSA-N bis($l^{2}-silanylidene)tantalum Chemical compound [Si]=[Ta]=[Si] MANYRMJQFFSZKJ-UHFFFAOYSA-N 0.000 description 6
- 238000001035 drying Methods 0.000 description 6
- 239000003822 epoxy resin Substances 0.000 description 6
- 229910021343 molybdenum disilicide Inorganic materials 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- VILCJCGEZXAXTO-UHFFFAOYSA-N 2,2,2-tetramine Chemical compound NCCNCCNCCN VILCJCGEZXAXTO-UHFFFAOYSA-N 0.000 description 5
- PIICEJLVQHRZGT-UHFFFAOYSA-N Ethylenediamine Chemical compound NCCN PIICEJLVQHRZGT-UHFFFAOYSA-N 0.000 description 5
- 239000004952 Polyamide Substances 0.000 description 5
- UKLDJPRMSDWDSL-UHFFFAOYSA-L [dibutyl(dodecanoyloxy)stannyl] dodecanoate Chemical compound CCCCCCCCCCCC(=O)O[Sn](CCCC)(CCCC)OC(=O)CCCCCCCCCCC UKLDJPRMSDWDSL-UHFFFAOYSA-L 0.000 description 5
- 239000012975 dibutyltin dilaurate Substances 0.000 description 5
- FJKROLUGYXJWQN-UHFFFAOYSA-N papa-hydroxy-benzoic acid Natural products OC(=O)C1=CC=C(O)C=C1 FJKROLUGYXJWQN-UHFFFAOYSA-N 0.000 description 5
- 229920002647 polyamide Polymers 0.000 description 5
- 229960004889 salicylic acid Drugs 0.000 description 5
- 238000010521 absorption reaction Methods 0.000 description 4
- 239000002390 adhesive tape Substances 0.000 description 4
- 230000001680 brushing effect Effects 0.000 description 4
- 238000011049 filling Methods 0.000 description 4
- 239000004033 plastic Substances 0.000 description 4
- 229920003023 plastic Polymers 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- 238000003756 stirring Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- CWQXQMHSOZUFJS-UHFFFAOYSA-N molybdenum disulfide Chemical compound S=[Mo]=S CWQXQMHSOZUFJS-UHFFFAOYSA-N 0.000 description 3
- 229910052982 molybdenum disulfide Inorganic materials 0.000 description 3
- 229910052814 silicon oxide Inorganic materials 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000003779 heat-resistant material Substances 0.000 description 2
- 239000003906 humectant Substances 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 229910021487 silica fume Inorganic materials 0.000 description 2
- 208000005156 Dehydration Diseases 0.000 description 1
- 229920000297 Rayon Polymers 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052810 boron oxide Inorganic materials 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000018044 dehydration Effects 0.000 description 1
- 238000006297 dehydration reaction Methods 0.000 description 1
- JKWMSGQKBLHBQQ-UHFFFAOYSA-N diboron trioxide Chemical compound O=BOB=O JKWMSGQKBLHBQQ-UHFFFAOYSA-N 0.000 description 1
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910052863 mullite Inorganic materials 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000009528 severe injury Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009044 synergistic interaction Effects 0.000 description 1
Classifications
-
- 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
- C09D1/00—Coating compositions, e.g. paints, varnishes or lacquers, based on inorganic substances
- C09D1/02—Coating compositions, e.g. paints, varnishes or lacquers, based on inorganic substances alkali metal silicates
- C09D1/04—Coating compositions, e.g. paints, varnishes or lacquers, based on inorganic substances alkali metal silicates with organic additives
-
- 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
- C09D5/00—Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects produced; Filling pastes
- C09D5/18—Fireproof paints including high temperature resistant paints
-
- 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
- C09D5/00—Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects produced; Filling pastes
- C09D5/34—Filling pastes
-
- 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
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
- C09D7/40—Additives
- C09D7/60—Additives non-macromolecular
- C09D7/61—Additives non-macromolecular inorganic
-
- 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
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
- C09D7/40—Additives
- C09D7/60—Additives non-macromolecular
- C09D7/63—Additives non-macromolecular organic
-
- 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
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
- C09D7/40—Additives
- C09D7/65—Additives macromolecular
-
- 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
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
- C09D7/40—Additives
- C09D7/70—Additives characterised by shape, e.g. fibres, flakes or microspheres
Landscapes
- Chemical & Material Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Wood Science & Technology (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Paints Or Removers (AREA)
Abstract
The invention provides a high-temperature-resistant protective coating repairing material and an online repairing method. The coating repair material comprises a component A and a component B, wherein the component A comprises coating matrix material powder; component B comprises a binder, a diluent, a radiation agent and a filler, or component B comprises a binder, a diluent, a radiation agent, a filler and a wetting agent; the binder comprises potassium silicate solution or sodium silicate solution, and the filler comprises silicon micropowder, beta-spodumene, boron nitride, silicon nitride, calcined alumina powder, zirconium silicate, metal boron powder and metal silicon powder. According to the invention, the components are cooperated to realize normal-temperature curing, when the coating of the aircraft is damaged, the damaged area can be directly repaired under the condition of not disassembling the aircraft, so that the online repair is realized, the cost is low, and the time and the labor are saved; the components in the filler are mutually cooperated, and meanwhile, the filler is matched with the binder, so that the high temperature resistance is realized, and the high temperature resistant filler can be stably used in an environment within 1100 ℃.
Description
Technical Field
The invention relates to the technical field of coating protection, in particular to a high-temperature-resistant protective coating repairing material and an online repairing method.
Background
In the flight process of the aerospace craft, the outer surface can be continuously exposed in a pneumatic heat environment, in order to reduce the impact and high-temperature damage of the external environment to the hot air flow of the aerospace craft during service and ensure the normal operation of the components in the aircraft, the surface of the aerospace craft is covered with a heat protection material for external protection so as to prevent heat from being transmitted to the inside, and then a radiation coating is prepared on the surface of the heat protection material so as to meet the high-temperature radiation and storage requirements of the heat protection material.
The coating and the heat protection material on the aircraft component are easy to damage in the transportation process of the aerospace aircraft, the coating and the heat protection material are also easy to damage in the technical processes of polishing, viscose and the like in the aircraft assembly process, the heat protection material leaks outside due to slight damage, the heat protection material is damaged due to severe damage, the protection function of the coating is lost, the heat protection system of the aircraft is possibly disabled, and the aircraft is seriously damaged. At present, the damage problem to the coating can only be solved through the mode of dismouting new heat protection material, namely the aircraft part that the coating damaged is dismantled the back and is changed the new part that the coating is intact, and is with high costs, and the assembly is wasted time and energy. Accordingly, there is a need in the art for a protective coating repair material that can be repaired on-line to repair damaged coatings without replacing and disassembling the damaged aircraft components while allowing the repaired coatings to meet the high temperature operating environment of the aircraft.
Disclosure of Invention
The invention provides a high-temperature-resistant protective coating repair material and an online repair method, which are used for solving the problems that after a coating on an aircraft is damaged, the repair can not be carried out, and only the damaged aircraft part of the coating can be disassembled, assembled and replaced.
In one aspect, the invention provides a high temperature resistant thermal protective coating repair material, which comprises a component A and a component B, wherein the component A comprises coating matrix material powder; the component B comprises a binder, a diluent, a radiation agent and a filler, or the component B comprises a binder, a diluent, a radiation agent, a filler and a wetting agent; the binder comprises a potassium silicate solution or a sodium silicate solution, and the filler comprises silicon micropowder, beta-spodumene, boron nitride, silicon nitride, calcined alumina powder, zirconium silicate, metal boron powder and metal silicon powder.
In some embodiments of the invention, the coating matrix material powder in component a is a thermal protective material powder comprising a light silica fiber preform reinforced modified phenolic aerogel composite powder, a silica fiber insulation tile powder, or an alumina fiber insulation tile powder.
In some embodiments of the invention, the diluent in component B is selected from one or more of absolute ethanol, isopropanol, n-butanol, toluene, acetone, and deionized water.
In some embodiments of the present invention, the radiation agent in the component B is the same as the radiation agent in the coating to be repaired. The radiating agent in component B may be selected from one or more of cobalt oxide, tantalum disilicide, molybdenum disulfide, and molybdenum disilicide.
In some embodiments of the invention, when component B comprises a wetting agent, the wetting agent is selected from glycerol, propylene glycol, or polyethylene glycol 200.
In some embodiments of the present invention, component B of the coating repair material comprises, in parts by weight, 80 to 90 parts of a binder, 10 to 20 parts of a diluent, 0 to 3 parts of a wetting agent, 15 to 30 parts of a radiation agent, and 20 to 30 parts of a filler.
In some embodiments of the present invention, the filler comprises 10 to 20 weight percent of the silica fume, beta-spodumene, boron nitride and silicon nitride, 70 to 80 weight percent of the calcined alumina powder and zirconium silicate, and 10 to 20 weight percent of the metal boron powder and metal silicon powder.
In some embodiments of the present invention, the filler comprises 3 to 5 weight percent of silica micropowder, beta-spodumene, boron nitride and silicon nitride: 2-3: 2-3: 2 to 3; the weight ratio of the calcined alumina powder to the zirconium silicate is 6-7: 3 to 4; the weight ratio of the metal boron powder to the metal silicon powder is 3-5: 5 to 7.
On the other hand, the invention also provides an online repairing method of the high-temperature-resistant thermal protection coating, which is applied to online repairing by the coating repairing material, and comprises the following steps: s1, crushing a coating matrix material to obtain a component A comprising coating matrix material powder; s2, uniformly mixing the binder, the diluent, the radiator and the filler or uniformly mixing the binder, the diluent, the radiator, the filler and the wetting agent to obtain a component B; s3, according to 50-70: weighing the component A and the component B according to the weight ratio of 30-50, and uniformly mixing to obtain a coating repair material; s4, repairing the damaged area of the coating by the coating repairing material, and standing at normal temperature until the coating repairing material is solidified; and S5, spraying the component B on a coating repair material curing area, standing at normal temperature until the coating repair material curing area is cured, spraying moisture-proof slurry, and standing at normal temperature to complete online repair.
In some embodiments of the present invention, the moisture resistant slurry includes a catalyst, a solvent, and a resin, the resin being an epoxy resin or a silicone resin. The catalyst may be selected from one or more of dibutyltin dilaurate, salicylic acid, tetramethylammonium hydroxide, polyamide, ethylenediamine and triethylenetetramine. The solvent may be one or more selected from absolute ethanol, isopropanol, n-butanol, toluene and acetone.
Compared with the prior art, the invention has the following beneficial effects:
(1) The high-temperature-resistant protective coating repairing material comprises a component A and a component B, wherein the component A comprises coating matrix material powder, the coating matrix material powder is heat-resistant material powder, and the addition of the heat-resistant material powder enables the repairing material to form a putty state, so that holes in a damaged area can be conveniently filled, the good matching property of the contact part between the damaged area and an undamaged area during repairing can be ensured, and the falling of the repairing material in the damaged area caused by separation of the damaged area and the undamaged area due to different thermal expansion coefficients and the like can be avoided; the component B comprises a diluent, a radiation agent, a filler and a potassium silicate solution or a sodium silicate solution, or the component B comprises the diluent, the radiation agent, the filler, a wetting agent and the potassium silicate solution or the sodium silicate solution, all the components are cooperated to realize normal-temperature curing, when a coating on an aircraft is damaged, a damaged area can be directly repaired, the repair can be completed after the repair is performed by normal-temperature curing, the complete machine on-line repair after the assembly of the aircraft heat protection material is completed is satisfied, a new part with a good coating is replaced after the damaged aircraft part is not required to be disassembled, the heat treatment is not required, the process is simple and feasible, the cost is low, and the time and the labor are saved; the invention uses potassium silicate solution or sodium silicate solution as binder, and as the potassium silicate solution or sodium silicate solution is water-based binder, deionized water can be selected as diluent, thereby widening the application range of the diluent; compared with resin curing, the dehydration curing speed of the potassium silicate solution or the sodium silicate solution is higher, the wetting agent can improve the surface tension and the permeability of the repairing material, improve the bonding strength of the repairing material and the coating matrix material, realize slow drying and prevent the repairing material from cracking caused by the excessively high drying speed.
(2) The filler comprises silicon micropowder, beta-spodumene, boron nitride, silicon nitride, calcined alumina powder, zirconium silicate, metal boron powder and metal silicon powder, the reaction activity of the repair material is lower, the silicon micropowder has higher activity and good dispersibility, the repair material is convenient to prepare into putty, the ceramic reaction activity of the repair material can be improved, namely, the ceramic of a coating obtained after repairing the repair material can be accelerated, the boron nitride, the metal silicon powder and the metal boron powder firstly undergo oxidation reaction along with the temperature rise to form boron oxide and silicon oxide, the silicon micropowder, the silicon oxide and the calcined alumina powder react with the temperature rise to form mullite, the silicon nitride can be partially oxidized to form a layer of oxide film on the surface of the silicon oxide film, the continuous oxidation can be prevented, the thermal shock resistance of the repair material coating can also be improved, the beta-spodumene is used as a fluxing agent, the crystal expansion is reduced, the crack of the repair material coating can be prevented, the zirconium silicate melting point is up to 2500 ℃, and when the potassium silicate solution or the sodium silicate solution is used as a binder, the zirconium silicate is well dispersed in the potassium silicate solution or the sodium silicate solution, the high-temperature resistance of the coating can be improved, and the high-temperature resistance of the high-temperature-resistant coating can be improved. The potassium silicate solution or the sodium silicate solution is matched with the filler, and the components in the filler are subjected to the mutual synergistic interaction, so that the high temperature resistance, the thermal shock resistance and the low cracking characteristic of the repairing material coating are endowed, the repairing material coating can be cured at normal temperature to realize on-line repairing, and the repairing material coating can be stably used in an environment within 1100 ℃.
(3) The component A coating matrix material powder is heat protection material powder, is preferably a common heat protection material, is more preferably consistent with the heat protection material under the coating to be repaired, realizes good matching performance, and prevents the repaired coating from falling off after the environmental temperature is changed; the specific choice of the diluent can be matched with potassium silicate solution or sodium silicate solution, so that the components of the repairing material are distributed more uniformly, the repairing material is not easy to crack after repairing, and the surface state of the coating obtained after curing is good; the radiation agent is the same as the radiation agent in the coating to be repaired, for example, the radiation agent can be one or more of cobalt oxide, tantalum disilicide, molybdenum disulfide and molybdenum disilicide, so that the radiation performance of the undamaged coating after the repair is consistent with that of the whole coating formed by the repaired coating can be ensured; the wetting agent is selected from glycerin, propylene glycol or polyethylene glycol 200, and besides being selected according to potassium silicate solution or sodium silicate solution, the wetting agent can better prevent cracking of the repair material in consideration of depth problem of damaged areas and the like, especially when the thickness to be repaired exceeds 0.5 mm; the design of the contents of all components in the repairing material, especially the design of the contents of all components in the filler, can ensure sprayability and radiation on one hand, can ensure the putty state of the repairing material on the other hand, is convenient for repairing damaged areas, and optimizes the stable use characteristics under normal-temperature curing and high-temperature conditions on the other hand.
(4) The online repairing method is based on the repairing material, the damaged area is repaired by the putty-state coating repairing material obtained by mixing the component A and the component B, the component B is sprayed after normal-temperature curing, the chromatic aberration between the undamaged area and the damaged area is eliminated, the moistureproof slurry is sprayed after normal-temperature curing, the moistureproof performance is endowed, and the repairing is completed after normal-temperature curing. The whole process of the repairing method adopts normal-temperature curing without heating, and can directly repair the damaged area under the condition of not disassembling the aircraft, thereby realizing on-line repairing, and having low cost, time saving and labor saving. The moisture-proof slurry is based on epoxy resin or organic silicon resin, the raw materials are easy to obtain, and the moisture-proof slurry is easy to solidify in the presence of a catalyst, so that a good moisture-proof function can be realized.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, various aspects related to the present invention will be described in detail with reference to the following specific embodiments, which are only for illustrating the present invention, but do not limit the scope and spirit of the present invention in any way.
Example 1:
the embodiment provides a high-temperature-resistant protective coating repair material which comprises a component A and a component B. Wherein component a comprises a coating matrix material powder; component B includes a binder, a diluent, a radiation agent and a filler or component B includes a binder, a diluent, a radiation agent, a filler and a wetting agent. The binder comprises potassium silicate solution or sodium silicate solution, and the filler comprises silicon micropowder, beta-spodumene, boron nitride, silicon nitride, calcined alumina powder, zirconium silicate, metal boron powder and metal silicon powder. In this embodiment, the wetting agent may be added as a component B or not, and specifically, whether to add or not may be selected according to actual requirements (for example, factors such as content ratio of each component, actual thickness to be repaired, etc.).
In this embodiment, the coating matrix material powder in the component a is a heat protecting material powder, preferably a common heat protecting material, more preferably consistent with the heat protecting material under the coating to be repaired, and the heat protecting material powder includes a light silica fiber preform reinforced modified phenolic aerogel composite powder, a silica fiber heat insulating tile powder or an alumina fiber heat insulating tile powder.
In this embodiment, the diluent in component B is selected from one or more of absolute ethanol, isopropanol, n-butanol, toluene, acetone, and deionized water. The radiation agent in component B is the same as the radiation agent in the coating to be repaired and can be, for example, one or more of cobalt oxide, tantalum disilicide, molybdenum disulfide and molybdenum disilicide. When component B includes a humectant, the humectant is selected from glycerin, propylene glycol or polyethylene glycol 200.
In the embodiment, the component B in the coating repair material comprises 80-90 parts by weight of binder, 10-20 parts by weight of diluent, 0-3 parts by weight of wetting agent, 15-30 parts by weight of radiating agent and 20-30 parts by weight of filler.
In the embodiment, the filler comprises 10-20% of silicon micropowder, beta-spodumene, boron nitride and silicon nitride, 70-80% of calcined alumina powder and zirconium silicate, and 10-20% of metal boron powder and metal silicon powder in percentage by weight.
In the embodiment, the weight ratio of the silicon micropowder, the beta-spodumene, the boron nitride and the silicon nitride in the filler is 3-5: 2-3: 2-3: 2 to 3; the weight ratio of the calcined alumina powder to the zirconium silicate is 6-7: 3 to 4; the weight ratio of the metal boron powder to the metal silicon powder is 3-5: 5 to 7.
The embodiment also provides an online repairing method of the high-temperature-resistant high-temperature heat protection coating, which is used for online repairing by the coating repairing material. The online repairing method of the embodiment comprises the following steps: s1, putting a coating matrix material into grinding equipment such as a grinder, grinding, and sieving with a 80-mesh sieve to obtain a component A comprising coating matrix material powder; s2, sieving the radiating agent and the filler through a 180-mesh sieve, and then mixing the binder, the diluent, the radiating agent and the filler or mixing the binder, the diluent, the radiating agent, the filler and the wetting agent, and uniformly grinding and mixing by using grinding equipment such as a ball mill and the like to obtain a component B; s3, according to 50-70: weighing the component A and the component B (namely, the weight ratio of the component A to the component B is 50-70:30-50) according to the weight ratio of 30-50, and uniformly mixing and stirring by using a high-speed dispersing machine or a stirrer to obtain a coating repairing material; s4, protecting the undamaged areas by using paper adhesive tapes, plastic cloths and the like; filling and repairing the damaged area of the coating by using tools such as a scraper, standing at normal temperature for not less than 12 hours until the damaged area of the coating is dried and solidified after repairing, wherein the severely damaged area can be repaired for multiple times, and the drying time after each repair is not less than 12 hours; after the area to be repaired is dried, polishing the repaired area to be smooth by using 180-mesh sand paper, and polishing the repaired area to be smooth by using 320-mesh sand paper; and S5, spraying or brushing the component B on a coating repair material curing area (namely a polished repair area) by using a spray gun or a brush, standing at normal temperature for about 24 hours until the coating repair material curing area is cured, spraying a moistureproof slurry, and standing at normal temperature to complete online repair.
In this embodiment, the moisture resistant slurry includes a catalyst, a solvent, and a resin. The resin is epoxy resin or organic silicon resin. The catalyst may be selected from one or more of dibutyltin dilaurate, salicylic acid, tetramethylammonium hydroxide, polyamide, ethylenediamine and triethylenetetramine. The solvent may be one or more selected from absolute ethanol, isopropanol, n-butanol, toluene and acetone.
After the online repair of the damaged area of the aircraft is carried out by applying the coating repair material of the embodiment, the performance indexes of the repaired coating are as follows: the highest temperature resistance can reach 1100 ℃, the water absorption is less than 0.1%, and the quartz lamp at 1100 ℃ has no cracking damage after 1000 seconds of examination.
Example 2:
the embodiment provides a high-temperature-resistant protective coating repair material which comprises a component A and a component B. Wherein component a comprises a coating matrix material powder; component B comprises a binder, a diluent, a radiation agent and a filler. The binder is potassium silicate solution, and the filler comprises silicon micropowder, beta-spodumene, boron nitride, silicon nitride, calcined alumina powder, zirconium silicate, metal boron powder and metal silicon powder.
In this embodiment, the thermal protection material under the coating to be repaired is a light quartz fiber preform reinforced modified phenolic aerogel composite material, the coating matrix material powder in component a is consistent with the light quartz fiber preform reinforced modified phenolic aerogel composite material powder, and the coating matrix material powder in component a is a light quartz fiber preform reinforced modified phenolic aerogel composite material powder.
In this embodiment, the diluent in component B is deionized water. The radiation agent in the coating to be repaired is cobalt oxide, the radiation agent in the component B is consistent with the cobalt oxide, and the radiation agent in the component B is cobalt oxide.
In this example, component B of the coating repair material comprises, in parts by weight, 80 parts binder, 20 parts diluent, 30 parts radiator and 30 parts filler.
In the embodiment, the filler comprises 20% of silicon micropowder, beta-spodumene, boron nitride and silicon nitride, 70% of calcined alumina powder and zirconium silicate, and 10% of metal boron powder and metal silicon powder in percentage by weight.
In the embodiment, the weight ratio of the silica micropowder, the beta-spodumene, the boron nitride and the silicon nitride in the filler is 3:2:2:3, a step of; the weight ratio of the calcined alumina powder to the zirconium silicate is 7:3, a step of; the weight ratio of the metal boron powder to the metal silicon powder is 3:7.
the embodiment also provides an online repairing method of the high-temperature-resistant high-temperature heat protection coating, which is used for online repairing by the coating repairing material. The online repairing method of the embodiment comprises the following steps: s1, putting a coating matrix material into grinding equipment such as a grinder, grinding, and sieving with a 80-mesh sieve to obtain a component A comprising coating matrix material powder; s2, sieving the radiation agent and the filler through a 180-mesh sieve, mixing the binder, the diluent, the radiation agent and the filler, and uniformly grinding and mixing by using grinding equipment such as a ball mill and the like to obtain a component B; s3, according to 50:50 weight ratio of the component A to the component B, and then uniformly mixing and stirring the components by using a high-speed dispersing machine or a stirrer to obtain a coating repair material; s4, protecting the undamaged areas by using paper adhesive tapes, plastic cloths and the like; filling and repairing the damaged area of the coating by using tools such as a scraper, standing at normal temperature for not less than 12 hours until the damaged area of the coating is dried and solidified after repairing, wherein the severely damaged area can be repaired for multiple times, and the drying time after each repair is not less than 12 hours; after the area to be repaired is dried, polishing the repaired area to be smooth by using 180-mesh sand paper, and polishing the repaired area to be smooth by using 320-mesh sand paper; and S5, spraying or brushing the component B on a coating repair material curing area (namely a polished repair area) by using a spray gun or a brush, standing at normal temperature for about 24 hours until the coating repair material curing area is cured, spraying a moistureproof slurry, and standing at normal temperature to complete online repair.
In this embodiment, the moisture resistant slurry includes a catalyst, a solvent, and a resin. The resin is epoxy resin or organic silicon resin. The catalyst may be selected from one or more of dibutyltin dilaurate, salicylic acid, tetramethylammonium hydroxide, polyamide, ethylenediamine and triethylenetetramine. The solvent is one or more selected from absolute ethanol, isopropanol, n-butanol, toluene, and acetone.
After the online repair of the damaged area of the aircraft is carried out by applying the coating repair material of the embodiment, the performance indexes of the repaired coating are as follows: the highest temperature resistance can reach 1100 ℃, the water absorption is less than 0.1%, and the quartz lamp at 1100 ℃ has no cracking damage after 1000 seconds of examination.
Example 3:
the embodiment provides a high-temperature-resistant protective coating repair material which comprises a component A and a component B. Wherein component a comprises a coating matrix material powder; component B comprises a binder, a diluent, a radiation agent, a wetting agent and a filler. The binder is sodium silicate solution, and the filler comprises silicon micropowder, beta-spodumene, boron nitride, silicon nitride, calcined alumina powder, zirconium silicate, metal boron powder and metal silicon powder.
In this embodiment, the thermal protection material under the coating to be repaired is a quartz fiber heat-insulating tile, and the coating matrix material powder in component a is consistent with the coating matrix material powder in component a, and the coating matrix material powder in component a is a quartz fiber heat-insulating tile powder.
In this embodiment, the diluent in component B is absolute ethanol. The radiation agent in the coating to be repaired is molybdenum disilicide, the radiation agent in the component B is consistent with the molybdenum disilicide, and the radiation agent in the component B is molybdenum disilicide. The wetting agent in the component B is polyethylene glycol 200.
In this example, component B of the coating repair material comprises 90 parts binder, 10 parts diluent, 3 parts wetting agent, 15 parts radiator and 20 parts filler by weight.
In the embodiment, the filler comprises 10% of silicon micropowder, beta-spodumene, boron nitride and silicon nitride, 80% of calcined alumina powder and zirconium silicate, and 10% of metal boron powder and metal silicon powder in percentage by weight.
In this example, the weight ratio of silica fume, beta-spodumene, boron nitride and silicon nitride in the filler was 4:2:2:2; the weight ratio of the calcined alumina powder to the zirconium silicate is 6:4, a step of; the weight ratio of the metal boron powder to the metal silicon powder is 5:5.
the embodiment also provides an online repairing method of the high-temperature-resistant high-temperature heat protection coating, which is used for online repairing by the coating repairing material. The online repairing method of the embodiment comprises the following steps: s1, putting a coating matrix material into grinding equipment such as a grinder, grinding, and sieving with a 80-mesh sieve to obtain a component A comprising coating matrix material powder; s2, sieving the radiation agent and the filler through a 180-mesh sieve, mixing the binder, the diluent, the radiation agent, the wetting agent and the filler, and uniformly grinding and mixing by using grinding equipment such as a ball mill and the like to obtain a component B; s3, according to the following steps of 60:40 weight ratio of the component A to the component B, and then uniformly mixing and stirring the components by using a high-speed dispersing machine or a stirrer to obtain a coating repair material; s4, protecting the undamaged areas by using paper adhesive tapes, plastic cloths and the like; filling and repairing the damaged area of the coating by using tools such as a scraper, standing at normal temperature for not less than 12 hours until the damaged area of the coating is dried and solidified after repairing, wherein the severely damaged area can be repaired for multiple times, and the drying time after each repair is not less than 12 hours; after the area to be repaired is dried, polishing the repaired area to be smooth by using 180-mesh sand paper, and polishing the repaired area to be smooth by using 320-mesh sand paper; and S5, spraying or brushing the component B on a coating repair material curing area (namely a polished repair area) by using a spray gun or a brush, standing at normal temperature for about 24 hours until the coating repair material curing area is cured, spraying a moistureproof slurry, and standing at normal temperature to complete online repair.
In this embodiment, the moisture resistant slurry includes a catalyst, a solvent, and a resin. The resin is epoxy resin or organic silicon resin. The catalyst may be selected from one or more of dibutyltin dilaurate, salicylic acid, tetramethylammonium hydroxide, polyamide, ethylenediamine and triethylenetetramine. The solvent is one or more selected from absolute ethanol, isopropanol, n-butanol, toluene, and acetone.
After the online repair of the damaged area of the aircraft is carried out by applying the coating repair material of the embodiment, the performance indexes of the repaired coating are as follows: the highest temperature resistance can reach 1100 ℃, the water absorption is less than 0.1%, and the quartz lamp at 1100 ℃ has no cracking damage after 1000 seconds of examination.
Example 4:
the embodiment provides a high-temperature-resistant protective coating repair material which comprises a component A and a component B. Wherein component a comprises a coating matrix material powder; component B comprises a binder, a diluent, a radiation agent, a wetting agent and a filler. The binder is potassium silicate solution, and the filler comprises silicon micropowder, beta-spodumene, boron nitride, silicon nitride, calcined alumina powder, zirconium silicate, metal boron powder and metal silicon powder.
In this embodiment, the thermal protection material under the coating to be repaired is an alumina fiber heat-insulating tile, and the coating matrix material powder in component a is consistent with the alumina fiber heat-insulating tile powder.
In this example, isopropanol is used as the diluent in component B. The radiating agents in the coating to be repaired are tantalum disilicide and cobalt oxide, the radiating agents in the component B are consistent with the tantalum disilicide and the cobalt oxide, and the radiating agents in the component B are tantalum disilicide and cobalt oxide. The wetting agent in the component B is propylene glycol.
In this example, component B of the coating repair material comprises, in parts by weight, 85 parts binder, 15 parts diluent, 1 part wetting agent, 20 parts radiator, and 25 parts filler.
In the embodiment, the filler comprises 10% of silicon micropowder, beta-spodumene, boron nitride and silicon nitride, 70% of calcined alumina powder and zirconium silicate, and 20% of metal boron powder and metal silicon powder in percentage by weight.
In the embodiment, the weight ratio of the silica micropowder, the beta-spodumene, the boron nitride and the silicon nitride in the filler is 3:3:2:2; the weight ratio of the calcined alumina powder to the zirconium silicate is 6.5:3.5; the weight ratio of the metal boron powder to the metal silicon powder is 4:6.
the embodiment also provides an online repairing method of the high-temperature-resistant high-temperature heat protection coating, which is used for online repairing by the coating repairing material. The online repairing method of the embodiment comprises the following steps: s1, putting a coating matrix material into grinding equipment such as a grinder, grinding, and sieving with a 80-mesh sieve to obtain a component A comprising coating matrix material powder; s2, sieving the radiation agent and the filler through a 180-mesh sieve, mixing the binder, the diluent, the radiation agent, the wetting agent and the filler, and uniformly grinding and mixing by using grinding equipment such as a ball mill and the like to obtain a component B; s3, according to 70:30 weight ratio of the component A to the component B, and then uniformly mixing and stirring the components by using a high-speed dispersing machine or a stirrer to obtain a coating repairing material; s4, protecting the undamaged areas by using paper adhesive tapes, plastic cloths and the like; filling and repairing the damaged area of the coating by using tools such as a scraper, standing at normal temperature for not less than 12 hours until the damaged area of the coating is dried and solidified after repairing, wherein the severely damaged area can be repaired for multiple times, and the drying time after each repair is not less than 12 hours; after the area to be repaired is dried, polishing the repaired area to be smooth by using 180-mesh sand paper, and polishing the repaired area to be smooth by using 320-mesh sand paper; and S5, spraying or brushing the component B on a coating repair material curing area (namely a polished repair area) by using a spray gun or a brush, standing at normal temperature for about 24 hours until the coating repair material curing area is cured, spraying a moistureproof slurry, and standing at normal temperature to complete online repair.
In this embodiment, the moisture resistant slurry includes a catalyst, a solvent, and a resin. The resin is epoxy resin or organic silicon resin. The catalyst may be selected from one or more of dibutyltin dilaurate, salicylic acid, tetramethylammonium hydroxide, polyamide, ethylenediamine and triethylenetetramine. The solvent is one or more selected from absolute ethanol, isopropanol, n-butanol, toluene, and acetone.
After the online repair of the damaged area of the aircraft is carried out by applying the coating repair material of the embodiment, the performance indexes of the repaired coating are as follows: the highest temperature resistance can reach 1100 ℃, the water absorption is less than 0.1%, and the quartz lamp at 1100 ℃ has no cracking damage after 1000 seconds of examination.
The present invention has been described with reference to specific embodiments, which are merely illustrative, and not intended to limit the scope of the invention, and those skilled in the art can make various modifications, changes or substitutions without departing from the spirit of the invention. Thus, various equivalent changes may be made according to this invention, which still fall within the scope of the invention.
Claims (10)
1. A high-temperature-resistant protective coating repairing material is characterized by comprising a component A and a component B,
wherein the component a comprises a coating matrix material powder;
the component B comprises a binder, a diluent, a radiation agent and a filler, or the component B comprises a binder, a diluent, a radiation agent, a filler and a wetting agent;
the binder comprises a potassium silicate solution or a sodium silicate solution, and the filler comprises silicon micropowder, beta-spodumene, boron nitride, silicon nitride, calcined alumina powder, zirconium silicate, metal boron powder and metal silicon powder.
2. The coated repair batch of claim 1, wherein the coating matrix material powder in component a is a thermal protection material powder comprising a light silica fiber preform reinforced modified phenolic aerogel composite powder, a silica fiber insulation tile powder, or an alumina fiber insulation tile powder.
3. The coated repair batch of claim 1, wherein the diluent in component B is selected from one or more of absolute ethanol, isopropanol, n-butanol, toluene, acetone, and deionized water.
4. The coated repair batch of claim 1 wherein the radiation agent in component B is the same as the radiation agent in the coating to be repaired.
5. The coated repair batch of claim 1, wherein when said component B comprises a wetting agent, said wetting agent is selected from the group consisting of glycerin, propylene glycol, and polyethylene glycol 200.
6. The coating repair material according to claim 1, wherein the component B in the coating repair material comprises 80 to 90 parts by weight of a binder, 10 to 20 parts by weight of a diluent, 0 to 3 parts by weight of a wetting agent, 15 to 30 parts by weight of a radiating agent and 20 to 30 parts by weight of a filler.
7. The coating repair material according to claim 1, wherein the filler comprises 10 to 20% by weight of fine silica powder, beta-spodumene, boron nitride and silicon nitride, 70 to 80% by weight of calcined alumina powder and zirconium silicate, and 10 to 20% by weight of metal boron powder and metal silicon powder.
8. The coating repair material according to claim 7, wherein the weight ratio of the silica powder, the beta-spodumene, the boron nitride and the silicon nitride in the filler is 3-5: 2-3: 2-3: 2 to 3; the weight ratio of the calcined alumina powder to the zirconium silicate is 6-7: 3 to 4; the weight ratio of the metal boron powder to the metal silicon powder is 3-5: 5 to 7.
9. An online repair method of a high temperature resistant thermal protective coating, characterized in that the online repair method uses the coating repair material according to any one of claims 1-8 for online repair, the online repair method comprising the following steps:
s1, crushing a coating matrix material to obtain a component A comprising coating matrix material powder;
s2, uniformly mixing the binder, the diluent, the radiator and the filler or uniformly mixing the binder, the diluent, the radiator, the filler and the wetting agent to obtain a component B;
s3, according to 50-70: weighing the component A and the component B according to the weight ratio of 30-50, and uniformly mixing to obtain a coating repair material;
s4, repairing the damaged area of the coating by the coating repairing material, and standing at normal temperature until the coating repairing material is solidified;
and S5, spraying the component B on a coating repair material curing area, standing at normal temperature until the coating repair material curing area is cured, spraying moisture-proof slurry, and standing at normal temperature to complete online repair.
10. The coated repair batch of claim 9, wherein the moisture resistant slurry comprises a catalyst, a solvent, and a resin, the resin being an epoxy or silicone resin.
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