CN104924718A - Metal surface high-temperature-resistant coating structure and applications thereof - Google Patents
Metal surface high-temperature-resistant coating structure and applications thereof Download PDFInfo
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- CN104924718A CN104924718A CN201410105857.XA CN201410105857A CN104924718A CN 104924718 A CN104924718 A CN 104924718A CN 201410105857 A CN201410105857 A CN 201410105857A CN 104924718 A CN104924718 A CN 104924718A
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Abstract
The invention discloses a metal surface high-temperature-resistant coating structure and applications thereof. The high-temperature-resistant coating material is composed of two layers namely an organic bottom layer and an inorganic surface layer; wherein the organic bottom layer is composed of epoxy resin, a polyamide curing agent, and a toughening agent (liquid rubber); and the inorganic surface layer is composed of flint clay, cordierite, aluminate cement and silica fume. The adhesion force of the provided high-temperature-resistant coating material is strong, which can sustain the washing of rocket imitated combustion-gas stream. The metal backside temperature does not exceed 120 DEG C, and the coating has an excellent performance on resisting high-temperature combustion-gas stream brushing and thermal insulation property.
Description
Technical field
The present invention relates to a kind of high-temperature resistant coating structure of metal surface; especially relate to a kind of for the reduction transmitting station back of the body temperature of rocket launching pad surface coating, the high-temperature resistant coating structure of protection rocket launching pad steel structure surface and application thereof, belong to high temperature resistant adiabatic protection field.
Background technology
Along with the development of space flight, aerospace cause, high-temperature resistant coating has opened up new application.Except the thermal protection of aircraft itself, domestic to ground installation as rocket launching pad too increases thermal protection measure.If transmitting station is coated with high-temperature resistant coating, metal surface can be made heat insulation, reduce thermal ablation and thermal shock, and prevent transmitting station under the effect of repeatedly thermal shock load, producing heat fatigue, heat cracks and thermal destruction, thus guarantee the reliability of transmitting station work, extend the service life of transmitting station.Abroad, the Ariane rocket flat pad that European Space Agency is positioned at Guyana, South America is concrete flat pad, it is better than organic ablation surface that ablation property is swept in this kind of transmitting station fire-resistant air-blowing of being constructed by Inorganic Non-metallic Materials, but shortcoming is thickness thick, Heavy Weight, and transmitting station cannot move.
Utilize special high temperature-resistant coating material and structure can carry out thermal protection to rocket launching pad, but at present, yet there are no relevant report about carrying out thermo-lag technology to transmitting station.
Summary of the invention
Technical problem to be solved by this invention increases thermal protection measure to ground installation rocket launching pad, and provide one can bear rocket wake flame and purge, back of the body temperature is no more than the structure of the high-temperaure coating of 120 DEG C.
Technical problem to be solved by this invention is achieved through the following technical solutions:
High-temperature resistant coating structure of the present invention, is made up of materials at two layers, and bottom is organic material, and top layer is inorganic material.
Bottom is made up of organic material, epoxy resin (mass ratio, lower same) 65 ~ 80%, curing agent polyamide 10 ~ 20%, flexibilizer liquid rubber 5 ~ 20%.The thickness of primer is 2 ~ 6mm.
Top layer is made up of inorganic material, flint clay 40 ~ 70%, cordierite 5 ~ 25%, aluminate cement 10 ~ 30%, silicon ash 2 ~ 10%.The thickness of skin-material is 6 ~ 14mm.
High-temperaure coating organic underlayer of the present invention and inorganic top layer gross thickness are 8 ~ 20mm.
Raw material used by the present invention can be bought from market and obtain, and its specification meets professional standard.Epoxy resin: model is SM828, curing agent polyamide: model is 650, manufacturer is the bright Chemical Co., Ltd. in Wuxi.Flexibilizer liquid rubber: model is number-average molecular weight 4000, manufacturer is Jinzhou Dalian Sheng Da product of rubber and plastic Co., Ltd.Aluminate cement: model is Secar71, manufacturer is Kai Nuosi (China) aluminate Technology Co., Ltd..Flint clay: granularity is 6-35M and 100-325M, manufacturer is Zibo jewel kiln Materials Co., Ltd.Cordierite: granularity is 0.5-1mm, Yanshi Guangming High-Tech Refractory Products Co., ltd. of manufacturer.Silicon ash: model 970, manufacturer is Shanghai Tian Kai silica flour Materials Co., Ltd.
High temperature-resistant coating material strong adhesion of the present invention, can bear rocket simulation gas-flow and wash away, metal backing surface temperature is no more than 120 DEG C, and coating has good heat-proof quality.
When the present invention applies, organic underlayer and inorganic top layer are coated on rocket launching pad successively.Because skin-material of the present invention is made up of Inorganic Non-metallic Materials, therefore the refractoriness of material is high, and intensity is large.When rocket launching is gone up to the air, coating is subject to the high temperature of gas-flow and washing away at a high speed, and the skin-material of coating can resistance to ablation and resistance to erosion, serves heat-blocking action, therefore protects rocket launching pad.
As can be seen here, will greatly reduce thermal ablation and the thermal shock of metallic matrix through the present invention, the back of the body temperature of metal will reduce greatly, thus effectively plays thermal protection effect to rocket launching pad.
Accompanying drawing explanation
The back temperature of Fig. 1: 10mm coating sample and the relation curve of ablation time;
The back temperature of Fig. 2: 15mm coating sample and the relation curve of ablation time;
Fig. 3: coating structure schematic diagram, in figure: 1-steel plate 2-organic layer 3-inorganic layer.
Detailed description of the invention
Further describe the present invention below in conjunction with specific embodiments and the drawings, advantage and disadvantage of the present invention will be more clear along with description.
The preparation of embodiment 1 high-temperature resistant coating structure
1. the preparation of organic underlayer: by epoxy resin SM828, curing agent polyamide 6 50, flexibilizer liquid rubber according to after the mixing of 7:2:1 mass ratio, be coated in the steel plate side of 190 × 120 × 5mm after rust cleaning on the surface, coating thickness is 2mm.
2. the preparation on inorganic top layer: first the mass ratio of the flint clay of 6-35M and 100-325M according to 1:1 is mixed, and then mixed flint clay is mixed according to mass ratio 12:3:4:1 with cordierite, aluminate cement, silicon ash.To be mixed evenly after, add water and stir 3min, amount of water is the 16%(mass fraction of top layer dosage).Before treating that organic underlayer does not solidify completely, skin-material is coated on primer.At thickness be 2mm bottom on coating thickness be the top layer of 8mm, preparation gross thickness be the high-temperaure coating of 10mm.
The thermal protection effect heat insulation to high-temperature resistant coating on metal foil is tested:
Adopt YA6804 type oxygen kerosene engine sample to be carried out to the test of testpieces back temperature, sample is that metal foil side scribbles high-temperature resistant coating, and the metal covering without coating is the back side.Experimental condition: engine combustion chamber pressure: Pc=1.4 ± 0.05MPa; Engine excess oxidizer coefficient: α=0.7 ± 0.03; Engine nozzle diameter: 65mm; Nozzle exit fuel gas temperature: 2210K; Nozzle exit combustion gas speed: 2390m/s; Chamber temperature: 3470K; The ablation test time: 5s/ part; Heat flow density: 13.1Mw/m
2.Wake flame when experimental condition is rocket launching analog purges situation, and flame purges the metal foil scribbling high-temperature resistant coating side.Test metal is without the temperature (back temperature) of coating side.The metalwork back temperature of 10mm thick coating and the relation of ablation time are as shown in Figure 1.As can be seen from the figure, the back of the body Wen Wei of the sample of 10mm thick coating is applied more than 100 DEG C.Result of the test shows, coating material of the present invention and structure strong adhesion, have good heat-proof quality, and protect steel plate ground.
Embodiment 2
The preparation of high-temperature resistant coating structure
1. the preparation of organic underlayer: by epoxy resin SM828, curing agent polyamide 6 50, flexibilizer liquid rubber according to after the mixing of 7:2:1 mass ratio, be coated in the steel plate side of 190 × 120 × 5mm after rust cleaning on the surface, coating thickness is 4mm.
2. the preparation on inorganic top layer: first the mass ratio of the flint clay of 6-35M and 100-325M according to 1:1 is mixed, and then mixed flint clay is mixed according to mass ratio 12:3:4:1 with cordierite, aluminate cement, silicon ash.To be mixed evenly after, add water and stir 3min, amount of water is the 16%(mass fraction of top layer dosage).Before treating that organic underlayer does not solidify completely, skin-material is coated on primer.At thickness be 4mm bottom on coating thickness be the top layer of 11mm, preparation gross thickness be the high-temperaure coating of 15mm.
The thermal protection effect heat insulation to high-temperaure coating on metal foil is tested:
Adopt YA6804 type oxygen kerosene engine sample to be carried out to the test of testpieces back temperature, sample is that metal foil side scribbles high-temperature resistant coating, and the metal covering without coating is the back side.Experimental condition: engine combustion chamber pressure: Pc=1.4 ± 0.05MPa; Engine excess oxidizer coefficient: α=0.7 ± 0.03; Engine nozzle diameter: 65mm; Nozzle exit fuel gas temperature: 2210K; Nozzle exit combustion gas speed: 2390m/s; Chamber temperature: 3470K; The ablation test time: 5s/ part; Heat flow density: 13.1Mw/m
2.Wake flame when experimental condition is rocket launching analog purges situation, and flame purges the metal foil scribbling high-temperature resistant coating side.Test metal is without the temperature (back temperature) of coating side.The metalwork back temperature of 15mm thick coating and the relation of ablation time are as shown in Figure 2.As can be seen from the figure, the back of the body Wen Wei of the sample of 15mm thick coating is applied more than 100 DEG C.Result of the test shows, coating material of the present invention and structure strong adhesion, have good heat-proof quality, and protect steel plate ground.
Claims (9)
1. a high-temperature resistant coating structure, is characterized in that: the organic underlayer set gradually in substrate surface and inorganic top layer materials at two layers composition.
2. according to high-temperature resistant coating structure according to claim 1, it is characterized in that: count in mass ratio, organic underlayer is made up of epoxy resin 65 ~ 80%, curing agent polyamide 10 ~ 20%, flexibilizer liquid rubber 5 ~ 20%.
3. according to high-temperature resistant coating structure according to claim 1, it is characterized in that: count in mass ratio, inorganic top layer is made up of flint clay, cordierite, aluminate cement and silicon ash, wherein, count in mass ratio, flint clay 40 ~ 70%, cordierite 5 ~ 25%, aluminate cement 10 ~ 30%, silicon ash 2 ~ 10%.
4. according to the high-temperature resistant coating structure described in claim 1 or 2, it is characterized in that: organic underlayer thickness is 2 ~ 6mm.
5. according to the high-temperature resistant coating structure described in claim 1 or 3, it is characterized in that: the thickness of inorganic skin-material is 6 ~ 14mm.
6. according to high-temperature resistant coating structure according to claim 1, it is characterized in that: high-temperature resistant coating organic underlayer and inorganic top layer gross thickness are 8 ~ 20mm.
7. according to high-temperature resistant coating structure according to claim 1, it is characterized in that: described substrate is metallic substrates.
8. according to high-temperature resistant coating structure according to claim 3, it is characterized in that: described flint clay is by two kinds of granularmetric compositions: a kind of granularity is between 6-35M, a kind of granularity is between 100-325M, and the flint clay mass ratio of two kinds of granularities is 1:1, and cordierite granularity is 0.5-1mm.
9. the high-temperature resistant coating structure of claim 1-8 described in any one is as a high-temperaure coating on transmitting station outer surface, is provided with organic underlayer, inorganic top layer successively in transmitting station outer surface.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105865262A (en) * | 2016-04-27 | 2016-08-17 | 北京航天发射技术研究所 | Ablation prevention method for inner surface for launching tube and launching tube applying method |
| CN107081940A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | A kind of structure of ship deck thermal protection coating and its application |
| CN113385766A (en) * | 2021-05-10 | 2021-09-14 | 西安交通大学 | High-temperature induction brazing device for ceramic matrix composite and carbon/carbon composite |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203004461U (en) * | 2012-12-04 | 2013-06-19 | 中国科学院大连化学物理研究所 | Thermal protection coating structure for transmitting platform |
| CN203844362U (en) * | 2014-03-20 | 2014-09-24 | 中国科学院大连化学物理研究所 | Structure of high-temperature-resistant coating for metal surface |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203004461U (en) * | 2012-12-04 | 2013-06-19 | 中国科学院大连化学物理研究所 | Thermal protection coating structure for transmitting platform |
| CN203844362U (en) * | 2014-03-20 | 2014-09-24 | 中国科学院大连化学物理研究所 | Structure of high-temperature-resistant coating for metal surface |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107081940A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | A kind of structure of ship deck thermal protection coating and its application |
| CN105865262A (en) * | 2016-04-27 | 2016-08-17 | 北京航天发射技术研究所 | Ablation prevention method for inner surface for launching tube and launching tube applying method |
| CN105865262B (en) * | 2016-04-27 | 2018-03-13 | 北京航天发射技术研究所 | Launch the launching tube of tube inner surface burn-out proof method and application this method |
| CN113385766A (en) * | 2021-05-10 | 2021-09-14 | 西安交通大学 | High-temperature induction brazing device for ceramic matrix composite and carbon/carbon composite |
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| CN104924718B (en) | 2017-01-25 |
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