CN107081941A - Structure and its application of a kind of metal surface with thermal protection coating material - Google Patents
Structure and its application of a kind of metal surface with thermal protection coating material Download PDFInfo
- Publication number
- CN107081941A CN107081941A CN201610087274.8A CN201610087274A CN107081941A CN 107081941 A CN107081941 A CN 107081941A CN 201610087274 A CN201610087274 A CN 201610087274A CN 107081941 A CN107081941 A CN 107081941A
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- Prior art keywords
- thermal protection
- fire
- protection coating
- coating material
- top layer
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/14—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a face layer formed of separate pieces of material which are juxtaposed side-by-side
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2255/00—Coating on the layer surface
- B32B2255/06—Coating on the layer surface on metal layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2255/00—Coating on the layer surface
- B32B2255/20—Inorganic coating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2255/00—Coating on the layer surface
- B32B2255/26—Polymeric coating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/304—Insulating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/306—Resistant to heat
- B32B2307/3065—Flame resistant or retardant, fire resistant or retardant
Abstract
The structure with thermal protection coating material and its application the invention discloses a kind of metal surface.The structure of thermal protection coating material of the present invention is made up of organic underlayer, fire-resistant light aggregate and inorganic top layer trilaminate material, wherein, the fire-resistant light aggregate part is embedded in organic underlayer, and a part is embedded among inorganic top layer.Organic underlayer is made up of epoxy resin, curing agent polyamide and toughener liquid rubber, and inorganic top layer is by waterglass, curing agent prodan, sand, cement composition.The thermal protection coating material of the present invention can bear rocket simulation combustion gas stream and wash away, and metal back side temperature is no more than 150 DEG C, and coating has good heat-proof quality.
Description
Technical field
The present invention relates to a kind of structure of metal surface with thermal protection coating material, it is used for fire more particularly, to one kind
The structure of the thermal protection coating material of the reduction rocket launching pad back of the body temperature of arrow transmitting station surface coating and its application, category
In the adiabatic protection field of high temperature resistant.
Background technology
With space flight, the development of aerospace cause, the new application field of thermal protection coating materials open.Except flying
Outside the thermal protection of row device in itself, the country also increases thermal protection measure to ground installation such as rocket launching pad.If
Rocket launching pad is coated with thermal protection coating material, metal surface can be made heat-insulated, thermal ablation and thermal shock is reduced,
And prevent rocket launching pad from producing heat fatigue, heat cracks and thermal destruction under the effect of multiple thermal shock load, so that
Ensure the reliability of rocket launching pad work, extend the service life of rocket launching pad.Abroad, European space flight
The Ariane rocket flat pad that office is located at South America Guyana is concrete flat pad, this kind of by inorganic non-metallic
It is better than organic ablation surface that ablation property is swept in the transmitting station fire-resistant air-blowing that material is constructed, but has the disadvantage that thickness is thick, weight
Amount is heavy, and transmitting station can not be moved.
Thermal protection can be carried out to rocket launching pad using special thermal protection coating material and structure, this heat is anti-
Shield coating material not only serves the effect of protection rocket launching pad, also solves all by inorganic non-metallic material
Construct weight weight, irremovable problem caused by transmitting station.
The content of the invention
Rocket wake flame purging can be born the invention provides one kind, heat of the metal back of the body temperature no more than 150 DEG C is prevented
The structure of coating material is protected, the structure of the thermal protection coating material can be sent out as thermal protection measure applied to rocket
She Tai surfaces.
The technical scheme is that：
A kind of structure of metal surface thermal protection coating material, be specially：Set gradually in substrate surface organic
Bottom, fire-resistant light aggregate and inorganic top layer, wherein, the fire-resistant light aggregate part is embedded in organic bottom
In layer, a part is embedded among inorganic top layer, and fire-resistant light aggregate is interspersed in organic underlayer and inorganic top layer
Form " pinning " structure.
Count in mass ratio, organic underlayer is by epoxy resin 65~80% (being preferably 65~75%), curing agent polyamide
10~20% (being preferably 15~20%), toughener liquid rubber 5~20% (being preferably 8~13%) composition；
Described epoxy resin is bis-phenol A glycidyl ether type epoxy resin, bisphenol F epoxy resin, bisphenol S
Epoxy resin, halogenated bisphenol A epoxy resin, hydrogenated bisphenol A epoxy resin, bisphenol-A D-ring oxygen tree fat,
It is more than one or both of Hydromethyl bisphenol Resin, epoxide number scope 0.2~0.6.
Described toughener liquid rubber is dienes liquid rubber, alkenes liquid rubber, polyurethanes liquid
More than one or both of body rubber, liquid silastic, liquid polysulfide rubber, liquid fluorubber, number is divided equally
Son amount scope is 3000~6000.
Fire-resistant light aggregate refractoriness is not less than 1200 DEG C, Al2O3Content is 10%~55%, fire-resistant light aggregate
Mesh number be 6~35 mesh.
Fire-resistant light aggregate is embedded in the middle of organic underlayer and inorganic top layer in the present invention, may be such that two layers of company
Connect even closer, meanwhile, the requirement to fire-resistant light aggregate is is resistant to high temperature, because aggregate is not exposed to
Surface, therefore requirement to aggregate is can be resistant to certain high temperature, preferably refractory temperature be not less than
1200 DEG C, simultaneously, it is contemplated that the requirement of cost, fire-resistant light aggregate be preferable over haydites of book structure, leca,
More than one or both of expanded perlite, but this is not intended to limit the selection to fire-resistant light aggregate.
Inorganic top layer be by waterglass, curing agent prodan, filler sand and cement composition, wherein, by matter
Amount is than meter, waterglass 20~40%, curing agent prodan 2~10%, filler sand 20~60%, filler cement
10~30%.
The modulus of waterglass is 1.5~3, and preferably modulus is 2~3；The sand was the sieve the following group after 35 mesh sieves
Part.
The quality of fire-resistant light aggregate and the mass ratio of organic underlayer are 1: (0.2~0.8).
The preparation of thermal protection coating material structure：
The preparation of organic underlayer：After epoxy resin, curing agent polyamide, toughener liquid rubber are mixed, apply
Cover on the surface of the substrate；
The preparation in fire-resistant light aggregate intermediate layer：The uniform spreading of fire-resistant light aggregate is pasted onto on organic underlayer；
The preparation on inorganic top layer：It is first that filler sand and cement mixing is uniform, it is then added to waterglass and solidification
In the mixed liquor of agent prodan, inorganic skin-material is obtained, inorganic skin-material is coated in fire-resistant light bone
On material.
The preparation on inorganic top layer：First by filler sand and cement according to (2~4): 1 mass ratio mixing is equal
It is even, mass ratio is then added to for (8~12): in 1 waterglass and curing agent prodan mixed liquor, is filled out
Expect sand and cement：The mass ratio of waterglass and curing agent prodan mixed liquor=(0.8~4): 1.
The thickness of organic underlayer is 2~6mm；The thickness on inorganic top layer is 3~14mm；Thermal protection coating material has
Machine bottom, fire-resistant light aggregate and inorganic top layer gross thickness are 5~20mm.
The structure that the present invention also provides above-mentioned thermal protection coating material is used for metal surface as thermal protection coating, tool
Body is：Organic bottom, fire-resistant light aggregate, inorganic top layer are set gradually in metal surface, wherein, it is described resistance to
A fiery aglite part is embedded in organic underlayer, and a part is embedded among inorganic top layer.
The metal surface is the outer surface of rocket launching pad.
Beneficial effects of the present invention：
The present invention provides a kind of structure of thermal protection coating, and the thermal protection coating structure is by organic underlayer, fire resisting
Aglite and inorganic top layer composition, wherein, a fire-resistant light aggregate part is embedded in organic underlayer, one
Divide and be embedded among inorganic top layer, form " pinning " structure.The structure is using refractoriness height, good heat-insulation effect
Fire-resistant light particles of aggregates as the second layer material be connected with machine bottom and inorganic top layer, when organic underlayer and nothing
After the materials at two layers solidification of machine top layer, fire-resistant light aggregate plays " pinning " effect physically, this " pinning "
Structure can preferably play a part of materials at two layers above and below link, material is preferably turned into an overall structure.
When the present invention is applied, organic underlayer, fire-resistant light aggregate and inorganic top layer are sequentially coated at rocket launching
On platform, because the composition of skin-material of the present invention is waterglass, curing agent prodan, filler sand and cement
Mixture, with mobility, be therefore particularly suitable for the planar structure of rocket launching pad.Water glass wherein used
Glass has cohesive force strong, and intensity is higher, the features such as heat-resist.Waterglass is when in use, it is necessary to add solidification
Agent prodan can just harden waterglass.The introducing of cement and sand, on the one hand can be further enhanced inorganic
The heat resistance on top layer, on the one hand can also increase the intensity on inorganic top layer.When rocket launching is gone up to the air, coating
By the high temperature of combustion gas stream and washing away for high speed, the skin-material of coating due to being inorganic refractory materials, this
Plant inorganic material and can be resistant to ablation and resistance to erosion, therefore serve heat-blocking action.Coating material of the present invention
Moment heat resisting temperature be 2500 DEG C, thermal protection coating material structure of the present invention will greatly reduce Metal Substrate
The thermal ablation and thermal shock of body so that metal back of the body temperature is lower, more heat-insulated, and coating shedding area is more after rocket launching
It is small, so as to effectively play thermal protection effect to rocket launching pad.
Brief description of the drawings
Fig. 1 is the structural representation of thermal protection coating material, in figure：1- steel plate 2- organic underlayer 3- fire resistings are light
The inorganic top layers of matter aggregate 4-.
Embodiment
The present invention is further described with reference to specific embodiments and the drawings, but is not limited claimed by the present invention
Scope.
Raw material used in the embodiment of the present invention can be commercially available from market, and its specification meets professional standard.
Cement：The portland cement of model 425, manufacturer is Zhengzhou Dengfeng Smelting Materials Co., Ltd..Epoxy resin：
Model SM828, curing agent polyamide：Model 650, manufacturer is the bright Chemical Co., Ltd. in Wuxi.
Toughener liquid rubber：Model number-average molecular weight 4000, manufacturer is that Jinzhou Dalian is contained up to product of rubber and plastic
Co., Ltd.Waterglass：Modulus is 3, and manufacturer is Jiashan of Zhejiang county Jing Hua chemical plant.Curing agent fluorine silicon
Sour sodium：28 mesh sieves are crossed, manufacturer is Liaoyang chemical plant.Fire-resistant light aggregate：6~35 mesh, factory
Family is Zibo jewel kiln Materials Co., Ltd.
The preparation of the thermal protection coating material of embodiment 1
1. the preparation of organic underlayer：By epoxy resin SM828, curing agent polyamide 6 50, toughener liquid rubber
After glue is mixed according to 7: 2: 1 ratios, on the steel plate for 190 × 120 × 5mm being coated in after derusting, paint removal,
Coating thickness is 2mm.
2. the preparation in fire-resistant light aggregate intermediate layer：The uniform spreading of fire-resistant light aggregate of 6~35 mesh is pasted onto
On organic underlayer, the quality of fire-resistant light aggregate and the mass ratio 1: 0.3 of organic underlayer.
3. the preparation on inorganic top layer：Filler sand and cement are well mixed according to 2: 1 mass ratio first,
It is then added in the mixed liquor of waterglass (M=3) and curing agent prodan according to 10: 1 mass ratios, filler
Sand and cement：Mass ratio=1 of waterglass containing curing agent: 1.Skin-material is coated in fire-resistant light bone
On material, coating thickness is 8mm, prepares the thermal protection coating that gross thickness is 10mm.To on metal foil
The heat-insulated thermal protection effect of thermal protection coating material is tested：
The test of testpieces back temperature is carried out to sample using YA6804 type oxygen kerosene engines, sample is
Metal foil side scribbles thermal protection coating material, is the back side without cated metal covering.Experimental condition：Hair
Motivation chamber pressure：Pc=1.4 ± 0.05MPa；Engine excess oxidizer coefficient：α=0.7 ± 0.03；Engine
Nozzle diameter：65mm；Engine fuel：Oxygen, kerosene；Gas flow outlet flow velocity：2390m/s；Combustion gas
Flow export temperature：2210K；The ablation test time：5s/ parts.Tail when experimental condition is rocket launching analog
Flame purges situation, and flame purges the metal foil for scribbling high temperature-resistant coating material side.Test the back of the body of metal foil
Face temperature.The metalwork back temperature measurement result that 10mm applies thickness is as shown in table 1.As can be seen from the table,
The back of the body temperature for coating the sample that 10mm applies thickness is 78.6 DEG C.Result of the test shows that thermal protection of the invention is applied
Layer material has good heat-proof quality with structure, and protects metal substrate.
The back temperature measurement result of the 10mm thermal protection coating material samples of table 1
The preparation of the thermal protection coating material of embodiment 2
1. the preparation of organic underlayer：By epoxy resin SM828, curing agent polyamide 6 50, toughener liquid rubber
After glue is mixed according to 7: 2: 1 ratios, on the steel plate for 190 × 120 × 5mm being coated in after derusting, paint removal,
Coating thickness is 4mm.
2. the preparation in fire-resistant light aggregate intermediate layer：The uniform spreading of fire-resistant light aggregate of 6~35 mesh is pasted onto
On organic underlayer, the quality of fire-resistant light aggregate and the mass ratio 1: 0.4 of organic underlayer.
3. the preparation on inorganic top layer：Filler sand and cement are mixed equal according to 2.5: 1 mass ratio first
It is even, it is then added in the mixed liquor of waterglass (M=3) and curing agent prodan according to 10: 1 mass ratios,
Filler sand and cement：Mass ratio=1 of waterglass containing curing agent: 1.Skin-material is coated in fire resisting light
On matter aggregate, coating thickness is 16mm, prepares the thermal protection coating that gross thickness is 20mm.
The thermal protection effect heat-insulated to high temperature-resistant coating material on metal foil is tested：
The test of testpieces back temperature is carried out to sample using YA6804 type oxygen kerosene engines, sample is
Metal foil side scribbles high temperature-resistant coating material, is the back side without cated metal covering.Experimental condition：Hair
Motivation chamber pressure：Pc=1.4 ± 0.05MPa；Engine excess oxidizer coefficient：α=0.7 ± 0.03；Engine
Nozzle diameter：65mm；Engine fuel：Oxygen, kerosene；Gas flow outlet flow velocity：2390m/s；Combustion gas
Flow export temperature：2210K；The ablation test time：10s/ parts.Tail when experimental condition is rocket launching analog
Flame purges situation, and flame purges the metal foil for scribbling high temperature-resistant coating material side.Test the back of the body of metal foil
Face temperature.The metalwork back temperature measurement result that 20mm applies thickness is as shown in table 2.As can be seen from the table,
The back of the body temperature for coating the sample that 20mm applies thickness is 84.4 DEG C.Result of the test shows that high temperature resistant of the invention is applied
Layer material has good heat-proof quality with structure, and protects metal substrate.
The back temperature measurement result of the 20mm thermal protection coating material samples of table 2
Claims (10)
1. a kind of metal surface structure of thermal protection coating material, it is characterised in that：Set successively in substrate surface
Organic underlayer, fire-resistant light aggregate and inorganic top layer are put, wherein, the fire-resistant light aggregate part is embedded in
In organic underlayer, a part is embedded among inorganic top layer.
2. according to the structure of the thermal protection coating material described in claim 1, it is characterised in that：Count in mass ratio,
Organic underlayer is by epoxy resin 65~80%, curing agent polyamide 10~20%, 5~20% groups of toughener liquid rubber
Into；
Fire-resistant light aggregate refractoriness is not less than 1200 DEG C, Al203Content is 10%~55%, fire-resistant light aggregate
Mesh number be 6~35 mesh.
3. according to the structure of the thermal protection coating material described in claim 1, it is characterised in that：Inorganic top layer is
By waterglass, curing agent prodan, filler sand and cement composition, wherein, count in mass ratio, waterglass
20~40%, curing agent prodan 2~10%, filler sand 20~60%, filler cement 10~30%.
4. according to the structure of the thermal protection coating material described in claim 3, it is characterised in that：The mould of waterglass
Number is 1.5~3, and preferably modulus is 2~3；The sand was component under sieve after 35 mesh sieves.
5. according to the structure of the thermal protection coating material described in claim 1, it is characterised in that：Fire-resistant light bone
The quality of material and the mass ratio of organic underlayer are 1: (0.2~0.8).
6. according to the structure of the thermal protection coating material described in claim 1, it is characterised in that：Thermal protection coating
The preparation of material structure：
The preparation of organic underlayer：After epoxy resin, curing agent polyamide, toughener liquid rubber are mixed, apply
Cover on the surface of the substrate；
The preparation in fire-resistant light aggregate intermediate layer：The uniform spreading of fire-resistant light aggregate is pasted onto on organic underlayer；
The preparation on inorganic top layer：It is first that filler sand and cement mixing is uniform, it is then added to waterglass and solidification
In the mixed liquor of agent prodan, inorganic skin-material is obtained, inorganic skin-material is coated in fire-resistant light bone
On material.
7. according to the structure of the thermal protection coating material described in claim 1, it is characterised in that：Inorganic top layer
Prepare：First by filler sand and cement according to (2~4): 1 mass ratio is well mixed, and is then added to matter
Amount ratio is (8: 12): in 1 waterglass and curing agent prodan mixed liquor, filler sand and cement:
The mass ratio of waterglass and curing agent prodan mixed liquor=(0.8~4): 1.
8. according to the structure of the thermal protection coating material described in claim 1, it is characterised in that：Organic underlayer is thick
Spend for 2~6mm；The thickness on inorganic top layer is 3~14mm；Thermal protection coating material organic underlayer, fire-resistant light
Aggregate and inorganic top layer gross thickness are 5~20mm.
9. a kind of structure of any thermal protection coating materials of claim 1-8 is used as heat for metal surface
The application of barrier material, it is characterised in that：Organic bottom, fire-resistant light bone are set gradually in metal surface
Material, inorganic top layer, wherein, the fire-resistant light aggregate part is embedded in organic underlayer, and a part is inlayed
Among inorganic top layer.
10. according to the application described in claim 9, it is characterised in that：The metal surface is rocket launching pad
Outer surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610087274.8A CN107081941A (en) | 2016-02-16 | 2016-02-16 | Structure and its application of a kind of metal surface with thermal protection coating material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610087274.8A CN107081941A (en) | 2016-02-16 | 2016-02-16 | Structure and its application of a kind of metal surface with thermal protection coating material |
Publications (1)
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Family
ID=59614059
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| CN201610087274.8A Pending CN107081941A (en) | 2016-02-16 | 2016-02-16 | Structure and its application of a kind of metal surface with thermal protection coating material |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108018585A (en) * | 2018-01-09 | 2018-05-11 | 范龙飞 | A kind of metal texture plate electroforming mould and method |
| CN109516819A (en) * | 2018-12-10 | 2019-03-26 | 河北利镔通用设备有限公司 | Grid section of refractory coating and preparation method thereof is fired on a kind of refractory coating, surface |
| CN109837032A (en) * | 2017-11-27 | 2019-06-04 | 中国科学院大连化学物理研究所 | A kind of structure and application of metal surface high tensile rapid curing adhesive |
| CN110553554A (en) * | 2019-09-03 | 2019-12-10 | 中国空空导弹研究院 | Light thermal protection structure for hypersonic missile |
| CN114798361A (en) * | 2022-05-11 | 2022-07-29 | 航天材料及工艺研究所 | Reusable flame-retardant ablation-resistant stealth compatible composite coating and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104691038A (en) * | 2013-12-06 | 2015-06-10 | 中国科学院大连化学物理研究所 | Structure of thermal protection coating used for steel structure surface and application thereof |
| CN204547235U (en) * | 2015-03-02 | 2015-08-12 | 中国科学院大连化学物理研究所 | A kind of structure of rocket launching pad high temperature-resistant coating material |
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2016
- 2016-02-16 CN CN201610087274.8A patent/CN107081941A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691038A (en) * | 2013-12-06 | 2015-06-10 | 中国科学院大连化学物理研究所 | Structure of thermal protection coating used for steel structure surface and application thereof |
| CN204547235U (en) * | 2015-03-02 | 2015-08-12 | 中国科学院大连化学物理研究所 | A kind of structure of rocket launching pad high temperature-resistant coating material |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109837032A (en) * | 2017-11-27 | 2019-06-04 | 中国科学院大连化学物理研究所 | A kind of structure and application of metal surface high tensile rapid curing adhesive |
| CN109837032B (en) * | 2017-11-27 | 2024-02-13 | 中国科学院大连化学物理研究所 | Structure and application of high-tensile-strength quick-curing adhesive for metal surface |
| CN108018585A (en) * | 2018-01-09 | 2018-05-11 | 范龙飞 | A kind of metal texture plate electroforming mould and method |
| CN109516819A (en) * | 2018-12-10 | 2019-03-26 | 河北利镔通用设备有限公司 | Grid section of refractory coating and preparation method thereof is fired on a kind of refractory coating, surface |
| CN110553554A (en) * | 2019-09-03 | 2019-12-10 | 中国空空导弹研究院 | Light thermal protection structure for hypersonic missile |
| CN114798361A (en) * | 2022-05-11 | 2022-07-29 | 航天材料及工艺研究所 | Reusable flame-retardant ablation-resistant stealth compatible composite coating and preparation method thereof |
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Application publication date: 20170822 |