CN109266212A - A kind of low density and high performance thermal protective coating - Google Patents
A kind of low density and high performance thermal protective coating Download PDFInfo
- Publication number
- CN109266212A CN109266212A CN201811040688.0A CN201811040688A CN109266212A CN 109266212 A CN109266212 A CN 109266212A CN 201811040688 A CN201811040688 A CN 201811040688A CN 109266212 A CN109266212 A CN 109266212A
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- Prior art keywords
- protective coating
- thermal protective
- high performance
- low density
- component
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Classifications
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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
- C09D183/00—Coating compositions based on macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing silicon, with or without sulfur, nitrogen, oxygen, or carbon only; Coating compositions based on derivatives of such polymers
- C09D183/04—Polysiloxanes
-
- 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
- C09D7/70—Additives characterised by shape, e.g. fibres, flakes or microspheres
Abstract
The present invention relates to a kind of low density and high performance thermal protective coatings, including component A and component B, the component A is the raw material of thermal protective coating, it include: matrix, anti-flaming thermal-insulation filler, reinforcing filler and solvent, the component B is curing agent, and addition curing agent obtains the low density and high performance thermal protective coating when use.Described matrix uses silicon rubber, and the anti-flaming thermal-insulation filler is glass hollow ball, and the reinforcing filler uses fume colloidal silica, and the solvent uses 120# industrial naptha, and the curing agent uses ethyl orthosilicate or positive silicic acid propyl ester.It is an advantage of the invention that density is low, high-elongation, compression strength are high, thermal conductivity is low.
Description
Technical field
The invention belongs to thermal protective coatings, and in particular to a kind of low density and high performance thermal protective coating.
Background technique
When the flying speed that the flying speed of aircraft is greater than 2.5 Mach and guided missile and rocket is greater than 3 Mach, they just have
Apparent Aerodynamic Heating, when flying speed is greater than 5 Mach, aircraft just has serious Aerodynamic Heating, referred to as " thermal boundary ".Thermal boundary
Have to the influence of aircraft bring: reducing strength of structural materials, has just been more than making for Al alloys andMg alloys when temperature is greater than 150 DEG C
Use temperature extremes；So that structure is generated thermal stress, makes structure severely deformed when serious and destroy；Make the reduction of body structure rigidity；Make
Internal temperature increases, and influences internal unit or propellant work.It is limited by structure and offline mode, aircraft outer surface thermal boundary
It not can avoid, can only take solar heat protection measure that overheat occurs to avoid aircraft and burns.
With the development in hypersonic technology field, the requirement of higher performance is proposed to rocket, guided missile, that is, is required to
Effective protection is carried out in the Aerodynamic Heating of flight course especially reentry stage to rocket and guided missile, but require to reduce passive quality,
Low cost improves payload ratio.Therefore requirements at the higher level are proposed to thermal protection technology.
Existing thermal protective coating has three aspects: 1. density is high.It is not able to satisfy aircraft lighting requirement.②
Comprehensive mechanical property is low.Elongation percentage, compressive property are low, are not able to satisfy long-term shelf appeal.3. thermal protective performance is poor.Resistance to ablation, every
Hot property is not able to satisfy aircraft solar heat protection index request.
Summary of the invention
Present invention aim to address the above problems, provide a kind of low density and high performance thermal protective coating, and use is advanced, mature
Material, by low density filler mechanical property enhance technology so that thermal protective coating have density is low, comprehensive mechanical property is high,
The good advantage of heat-proof quality.
To achieve the above object, the invention provides the following technical scheme:
A kind of low density and high performance thermal protective coating, including component A and component B, the component A are the raw material of thermal protective coating,
It include: matrix, anti-flaming thermal-insulation filler, reinforcing filler and solvent, the component B is curing agent, and addition curing agent obtains when use
The low density and high performance thermal protective coating.
Further, described matrix uses silicon rubber, and the anti-flaming thermal-insulation filler is glass hollow ball, the reinforcing filler
Using fume colloidal silica, the solvent uses 120# industrial naptha, and the curing agent uses ethyl orthosilicate or positive silicic acid third
Ester.
Further, the formula of the thermal protective coating are as follows: by weight, A:100 parts of silicon rubber of component, 50~80 parts hollow
Glass marble, 20~50 parts of fume colloidal silicas, 100 parts of 120# industrial napthas；Component B:3~6 part curing agent.
Further, the silicone rubber matrix range of viscosities of the thermal protective coating is described in 6000~10000Pas
The glass hollow ball density range of thermal protective coating is in 0.3~0.6g/cm3, the fume colloidal silica surface area of the thermal protective coating
For 170~250m2/g.
Further, the silicone rubber matrix viscosity of the thermal protective coating is preferably 7000Pas, the thermal protective coating
Glass hollow ball density be preferably 0.46g/cm3, the fume colloidal silica surface area of the thermal protective coating is preferably 230m2/
g。
Further, the aircraft solar heat protection that the thermal protective coating is suitable for Mach number 3~12 uses.
The beneficial effects of the present invention are:
Density is low: for prior art coating density generally in 0.8~1.2g/cm3, thermal protective coating density of the present invention is minimum
It can reach 0.5g/cm3；High-elongation: generally 10% or so, thermal protective coating of the present invention prolongs prior art coating elongation percentage
Rate is stretched greater than 30%；Compression strength: for prior art coating compression strength generally in 1MPa or so, thermal protective coating of the present invention is anti-
Compressive Strength is greater than 2MPa；Thermal conductivity: prior art coating thermal conductivity is generally in 0.2W/m K or so, thermal protective coating of the present invention
Thermal conductivity is less than 0.14 thermal conductivity.
Specific embodiment
The present invention uses advanced, mature material, enhances technology by low density filler mechanical property, develops a kind of close
Spend the aircraft thermal protective coating that low, comprehensive mechanical property is high, heat-proof quality is good.
Low-density, high-performance thermal protective coating are A+B formula.Component A includes matrix, anti-flaming thermal-insulation filler, reinforcing filler, molten
Agent etc..B component is curing agent, and addition curing agent obtains the low density and high performance thermal protective coating when use.
(1) the general Application Range of basis material includes epoxy resin, phenolic resin, silicone rubber-modified epoxy resin, silicon
Rubber etc..In view of aircraft may work under high/low temperature cycling condition, the present invention selects silicon rubber as matrix, is applicable in
Temperature possesses more wide in range use temperature range at -90 DEG C~450 DEG C.Range of viscosities is in 6000~10000Pas.
(2) since silicon rubber is a kind of combustible material, need to increase a kind of anti-flaming thermal-insulation filler, general Application Range includes
Glass fibre, carbon fiber, aromatics fiber, silicon carbide fibre, phenolic aldehyde hollow sphere, glass hollow ball etc..In view of lighting requires,
The present invention selects glass hollow ball.Density range is in 0.3~0.6g/cm3.
(3) in order to increase Mechanical Properties of Silicone Rubber, improve the interface binding power of filler and silicon rubber, need to add surface and change
Property agent, general Application Range includes: metal powder, nano powder etc..The present invention selects fume colloidal silica.Surface area 170~
250m2/g。
(4) for adjust silicon rubber curing reaction in conduct heat and heat dissipation, so that reaction molecular is evenly distributed, increase it is intermolecular
The chance of collision and contact, needs to be added solvent and is adjusted.The present invention selects 120# industrial naptha.
(5) curing agent.The raw rubber of silicon rubber needs to be added a certain proportion of particular agent, and can to generate cross-linking reaction solidifying
Gu becoming the solid material of elasticity.General Application Range includes: Sulfur, selenium, tellurium, sulfur-containing compound, metal oxide, peroxidating
Object, resin, quinones and amine etc..The present invention selects ethyl orthosilicate or positive silicic acid propyl ester.
(6) currently preferred thermal protective coating is formulated scheme are as follows: component A: 100 parts of silicon rubber, 50~80 parts of hollow glass
Ball, 20~50 parts of fume colloidal silicas, 100 parts of 120# industrial napthas；B component: 3~6 parts of curing agent.
(7) table 1 is the performance parameter table of low density and high performance thermal protective coating after solidifying.
The performance parameter of 1 low density and high performance thermal protective coating of table
| Serial number | Performance class | Performance indicator |
| 1 | Density (g/cm3) | 0.5~0.7 |
| 2 | Tensile strength (MPa) | ≥1.5 |
| 3 | Elongation at break (%) | >=30% |
| 4 | Thermal conductivity (W/mK) | ≤0.14 |
| 5 | Specific heat capacity (J/gK) | ≥1.2 |
| 6 | Tensile-sbear strength (MPa) | ≥1.5 |
| 7 | Shao's A hardness | ≥75 |
| 8 | Compression strength (MPa) | ≥2 |
Compared with prior art, advantage of the present invention are as follows:
1. density is low: prior art coating density is generally in 0.8~1.2g/cm3, and thermal protective coating density of the present invention is most
It is low to can reach 0.5g/cm3.
2. high-elongation: prior art coating elongation percentage is generally 10% or so, thermal protective coating elongation percentage of the present invention
Greater than 30%.
3. compression strength: prior art coating compression strength is generally in 1MPa or so, thermal protective coating resistance to compression of the present invention
Intensity is greater than 2MPa.
4. thermal conductivity: prior art coating thermal conductivity is generally in 0.2W/m K or so, thermal protective coating thermal conductivity of the present invention
Rate is less than 0.14 thermal conductivity.
The present invention is suitable for the aircraft solar heat protection of Mach number 3~12.
The content not being described in detail in the present invention is the prior art.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (6)
1. a kind of low density and high performance thermal protective coating, which is characterized in that including component A and component B, the component A be that solar heat protection applies
The raw material of layer, comprising: matrix, anti-flaming thermal-insulation filler, reinforcing filler and solvent, the component B are curing agent, and addition is solid when use
Agent obtains the low density and high performance thermal protective coating.
2. a kind of low density and high performance thermal protective coating according to claim 1, which is characterized in that described matrix uses silicon rubber
Glue, the anti-flaming thermal-insulation filler are glass hollow ball, and the reinforcing filler uses fume colloidal silica, and the solvent uses 120#
Industrial naptha, the curing agent use ethyl orthosilicate or positive silicic acid propyl ester.
3. a kind of low density and high performance thermal protective coating according to claim 2, which is characterized in that the thermal protective coating is matched
Side are as follows: by weight, A:100 parts of silicon rubber of component, 50~80 parts of hollow glass balls, 20~50 parts of fume colloidal silicas, 100 parts
120# industrial naptha；Component B:3~6 part curing agent.
4. a kind of low density and high performance thermal protective coating according to claim 2, which is characterized in that the thermal protective coating
Silicone rubber matrix range of viscosities in 6000~10000Pas, the glass hollow ball density range of the thermal protective coating is 0.3
~0.6g/cm3, the fume colloidal silica surface area of the thermal protective coating is 170~250m2/g。
5. a kind of low density and high performance thermal protective coating according to claim 4, which is characterized in that the silicon of the thermal protective coating
Rubber matrix viscosity is preferably 7000Pas, and the glass hollow ball density of the thermal protective coating is preferably 0.46g/cm3, described
The fume colloidal silica surface area of thermal protective coating is preferably 230m2/g。
6. a kind of low density and high performance thermal protective coating according to any one of claims 1 to 5, which is characterized in that described anti-
The aircraft solar heat protection that hot coating is suitable for Mach number 3~12 uses.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811040688.0A CN109266212A (en) | 2018-09-07 | 2018-09-07 | A kind of low density and high performance thermal protective coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811040688.0A CN109266212A (en) | 2018-09-07 | 2018-09-07 | A kind of low density and high performance thermal protective coating |
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| Publication Number | Publication Date |
|---|---|
| CN109266212A true CN109266212A (en) | 2019-01-25 |
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| CN201811040688.0A Pending CN109266212A (en) | 2018-09-07 | 2018-09-07 | A kind of low density and high performance thermal protective coating |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112500786A (en) * | 2020-11-18 | 2021-03-16 | 北京星航机电装备有限公司 | High-heat-resistance silicone rubber coating and preparation method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090018261A1 (en) * | 2007-07-13 | 2009-01-15 | Momentive Performance Materials, Inc. | Curable and cured silicone rubber compositions and methods therefor |
| CN106633908A (en) * | 2016-12-26 | 2017-05-10 | 广州市高士实业有限公司 | Novel environment-friendly double component heat insulation silicone rubber and preparation method thereof |
| CN107760194A (en) * | 2017-10-12 | 2018-03-06 | 上海航天精密机械研究所 | A kind of anti-heat insulating coat of silicon rubber base and preparation method thereof |
| CN107903823A (en) * | 2017-12-01 | 2018-04-13 | 湖北航聚科技有限公司 | Outer thermal protective coating of a kind of lightening fire resistant and preparation method thereof |
| CN108410125A (en) * | 2018-04-24 | 2018-08-17 | 航天特种材料及工艺技术研究所 | A kind of anti-heat-insulation integrative resin combination, anti-heat-insulation integrative resin base ablator and preparation method thereof |
-
2018
- 2018-09-07 CN CN201811040688.0A patent/CN109266212A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090018261A1 (en) * | 2007-07-13 | 2009-01-15 | Momentive Performance Materials, Inc. | Curable and cured silicone rubber compositions and methods therefor |
| CN106633908A (en) * | 2016-12-26 | 2017-05-10 | 广州市高士实业有限公司 | Novel environment-friendly double component heat insulation silicone rubber and preparation method thereof |
| CN107760194A (en) * | 2017-10-12 | 2018-03-06 | 上海航天精密机械研究所 | A kind of anti-heat insulating coat of silicon rubber base and preparation method thereof |
| CN107903823A (en) * | 2017-12-01 | 2018-04-13 | 湖北航聚科技有限公司 | Outer thermal protective coating of a kind of lightening fire resistant and preparation method thereof |
| CN108410125A (en) * | 2018-04-24 | 2018-08-17 | 航天特种材料及工艺技术研究所 | A kind of anti-heat-insulation integrative resin combination, anti-heat-insulation integrative resin base ablator and preparation method thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112500786A (en) * | 2020-11-18 | 2021-03-16 | 北京星航机电装备有限公司 | High-heat-resistance silicone rubber coating and preparation method thereof |
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