CN203004461U - Thermal protection coating structure for transmitting platform - Google Patents
Thermal protection coating structure for transmitting platform Download PDFInfo
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- CN203004461U CN203004461U CN 201220660901 CN201220660901U CN203004461U CN 203004461 U CN203004461 U CN 203004461U CN 201220660901 CN201220660901 CN 201220660901 CN 201220660901 U CN201220660901 U CN 201220660901U CN 203004461 U CN203004461 U CN 203004461U
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Abstract
The utility model discloses a thermal protection coating material structure for a transmitting platform. The thermal protection coating material structure disclosed by the utility model is formed by an organic bottom layer and an organic-inorganic composite surface layer, wherein the organic bottom layer is formed by epoxy resin, a polyamide curing agent and a liquid rubber toughening agent, and the organic-inorganic composite surface layer is formed by an epoxy resin organic rubber, a polyamide curing agent, sands and cement. The thermal protection coating material disclosed by the utility model can endure washing of a simulated rocket gas flow, temperature of a metal back is not more than 200 DEG C, and the thermal protection coating material has good heat insulation performance.
Description
Technical field
The utility model relates to the thermal protection coating structure of rocket launching pad, especially relates to a kind of thermal protection coating structure and application thereof of the reduction transmitting station back of the body temperature that applies for rocket launching pad surface, belongs to high temperature resistant adiabatic protection field.
Background technology
Along with the development of space flight, aerospace cause, thermal protection coating has been opened up new application.Except the thermal protection of aircraft itself, domestic ground installation such as rocket launching pad have also been increased the thermal protection measure.If transmitting station is coated with thermal protection coating, can make the metal surface heat insulation, reduce thermal ablation and thermal shock, and prevent that transmitting station from repeatedly producing heat fatigue, heat cracks and thermal destruction under the thermal shock load, thereby 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 the concrete flat pad, it is better than organic ablation coating that the anti-combustion gas of transmitting station that this class is constructed by Inorganic Non-metallic Materials purges ablation property, but it is thick that shortcoming is thickness, Heavy Weight, and transmitting station can't move.
Utilize special thermal protection coating material and structure to carry out thermal protection to rocket launching pad, but at present, yet there are no relevant report about transmitting station is carried out thermo-lag technology.
The utility model content
Technical problem to be solved in the utility model is that the ground installation rocket launching pad is increased the thermal protection measure, provides a kind of rocket wake flame that can bear to purge, and back of the body temperature is no more than the structure of the thermal protection coating of 200 ℃.
Technical problem to be solved in the utility model is achieved through the following technical solutions:
The utility model thermal protection coating structure, the organic underlayer and the organic and inorganic composite skins materials at two layers that set gradually in substrate surface form.Described substrate is metallic substrates.Bottom is organic material, and the top layer is composite organic-inorganic material.
Bottom is comprised 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.
The composite that the top layer is comprised of organic material and inorganic material, organic gel epoxy resin 40～60%, polyurethane curing agent 10～20%, filler sand 15～30%, filler cement 5～15%.The thickness of skin-material is 3～14mm.
The utility model thermal protection coating organic underlayer and organic and inorganic composite skins gross thickness are 5～20mm.
The utility model raw material used can be bought from market and obtain, and its specification meets industry standard.Cement: model is 425 portland cements, and manufacturer is Zhengzhou Dengfeng Smelting Materials Co., Ltd..Epoxy resin: model is SM828, the curing agent polyamide: model is 650, and manufacturer is Wuxi bright chemical industry Co., Ltd.The flexibilizer liquid rubber: model is number-average molecular weight 4000, and manufacturer is that Jinzhou Dalian is contained and to be reached product of rubber and plastic Co., Ltd.Organic gel epoxy resin: model is SM815, polyurethane curing agent: model is 735, and manufacturer is Sanmu Group Co., Ltd., Jiangsu.
When the utility model is used, be coated in successively organic underlayer and organic and inorganic composite skins on rocket launching pad, because the present invention adopts said structure, when coating is subject to the high temperature of gas-flow and washing away at a high speed, at first the skin-material of coating material has a physics heat absorption sharply, and the beginning chemical breakdown, temperature rises and to internal heat transfer.Residue after decomposition forms the carbon residue layer, and it plays heat-blocking action and resistance to erosion effect.Therefore, the high polymer ablation resistance that these carbon forming rates are high, the carbon residue layer is closely knit is good.
This shows, 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, thereby effectively rocket launching pad is played the thermal protection effect.
Description of drawings
Fig. 1: the back temperature of 6mm coating sample and the relation curve of ablation time;
Fig. 2: the back temperature of 15mm coating sample and the relation curve of ablation time.
Fig. 3 is the utility model structural representation.
Wherein, 1, substrate, 2, organic underlayer, 3, organic and inorganic composite skins.
The specific embodiment
Further describe the present invention below in conjunction with specific embodiments and the drawings, advantage and disadvantage of the present utility model will be more clear along with description.
The preparation of embodiment 1 thermal protection coating structure
1. the preparation of organic underlayer: after epoxy resin SM828, curing agent polyamide 6 50, flexibilizer liquid rubber are mixed according to the 7:2:1 ratio, be coated on the steel plate of 190 * 120 * 5mm after rust cleaning, paint removal, coating thickness is 2mm.
2. the preparation of organic and inorganic composite skins: at first filler sand and the cement ratio according to 2:1 is mixed, then add in organic gel epoxy resin SM815 and the epoxy glue of polyurethane curing agent 735 according to the 3:1 ratio, the ratio of solid and liquid is 3:1.Before treating that organic underlayer does not solidify fully, skin-material is coated on primer.Be that on the bottom of 2mm, coating thickness is the top layer of 4mm at thickness, the preparation gross thickness is the thermal protection coating of 6mm.
The thermal protection effect that thermal protection coating on metal foil is heat insulation is tested:
Adopt YA6804 type oxygen kerosene engine sample to be carried out the test of testpieces back temperature, sample is that metal foil one side scribbles thermal protection coating, is the back side without the metal covering of coating.Experimental condition: engine combustion chamber pressure: Pc=1.4 ± 0.05MPa; Engine excess oxidizer coefficient: α=0.7 ± 0.03; Engine nozzle diameter: 65mm; The ablation test time: 5s/ spare.Wake flame when experimental condition is rocket launching analog purges situation, and flame purges the metal foil that scribbles thermal protection coating one side.Test respectively the back temperature of 2 T1 and T2.The relation of the back temperature of 6mm thick coating and ablation time as shown in Figure 1.As can be seen from the figure, the back of the body Wen Wei of the sample of coating 6mm thick coating is over 100 ℃.Result of the test shows, coating material of the present invention and structure have good heat-proof quality, and have protected the steel plate ground.
The preparation of embodiment 2 thermal protection coating structures
1. the preparation of organic underlayer: after epoxy resin SM828, curing agent polyamide 6 50, flexibilizer liquid rubber are mixed according to the 7:2:1 ratio, be coated on the steel plate of 190 * 120 * 5mm after rust cleaning, paint removal, coating thickness is 4mm.
2. the preparation of organic and inorganic composite skins: at first filler sand and the cement ratio according to 2:1 is mixed, then add in organic gel epoxy resin SM815 and the epoxy glue of polyurethane curing agent 735 according to the 3:1 ratio, the ratio of solid and liquid is 3:1.Before treating that organic underlayer does not solidify fully, skin-material is coated on primer.Be that on the bottom of 4mm, coating thickness is the top layer of 11mm at thickness, the preparation gross thickness is the thermal protection coating of 15mm.The thermal protection effect that thermal protection coating on metal foil is heat insulation is tested:
Adopt YA6804 type oxygen kerosene engine sample to be carried out the test of testpieces back temperature, sample is that metal foil one side scribbles thermal protection coating, is the back side without the metal covering of coating.Experimental condition: engine combustion chamber pressure: Pc=1.4 ± 0.05MPa; Engine excess oxidizer coefficient: α=0.7 ± 0.03; Engine nozzle diameter: 65mm; The ablation test time: 5s/ spare.Wake flame when experimental condition is rocket launching analog purges situation, and flame purges the metal foil that scribbles thermal protection coating one side.Test respectively the back temperature of 2 T1 and T2.The relation of the back temperature of 15mm thick coating and ablation time as shown in Figure 2.As can be seen from the figure, the back of the body Wen Wei of the sample of coating 15mm thick coating is over 100 ℃.Result of the test shows, coating material of the present utility model and structure have good heat-proof quality, and have protected the steel plate ground.
Claims (5)
1. a transmitting station with the structure of thermal protection coating, is characterized in that: the organic underlayer (2) and organic and inorganic composite skins (3) the materials at two layers composition that set gradually in substrate (1) surface.
2. according to the structure of thermal protection coating claimed in claim 1, it is characterized in that: organic underlayer thickness is 2 ~ 6mm.
3. according to the structure of thermal protection coating claimed in claim 1, it is characterized in that: the thickness of organic and inorganic composite skins material is 3 ~ 14mm.
4. according to the structure of claim 1,2 or 3 described thermal protection coatings, it is characterized in that: thermal protection coating organic underlayer and organic and inorganic composite skins gross thickness are 5 ~ 20mm.
5. according to the structure of thermal protection coating claimed in claim 1, it is characterized in that: described substrate is metallic substrates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220660901 CN203004461U (en) | 2012-12-04 | 2012-12-04 | Thermal protection coating structure for transmitting platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220660901 CN203004461U (en) | 2012-12-04 | 2012-12-04 | Thermal protection coating structure for transmitting platform |
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| CN203004461U true CN203004461U (en) | 2013-06-19 |
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| CN 201220660901 Expired - Lifetime CN203004461U (en) | 2012-12-04 | 2012-12-04 | Thermal protection coating structure for transmitting platform |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103847189A (en) * | 2012-12-04 | 2014-06-11 | 中国科学院大连化学物理研究所 | Structure of thermal protective coating for launching pad and application of structure |
| CN104691065A (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 metal surface and application thereof |
| 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 |
| CN104924704A (en) * | 2014-03-20 | 2015-09-23 | 中国科学院大连化学物理研究所 | High-temperature-resistant coating structure for steel structure surface and applications thereof |
| CN104924718A (en) * | 2014-03-20 | 2015-09-23 | 中国科学院大连化学物理研究所 | Metal surface high-temperature-resistant coating structure and applications thereof |
-
2012
- 2012-12-04 CN CN 201220660901 patent/CN203004461U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103847189A (en) * | 2012-12-04 | 2014-06-11 | 中国科学院大连化学物理研究所 | Structure of thermal protective coating for launching pad and application of structure |
| CN103847189B (en) * | 2012-12-04 | 2016-05-11 | 中国科学院大连化学物理研究所 | Structure and the application thereof of thermal protection coating for a kind of transmitting station |
| CN104691065A (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 metal surface and application thereof |
| 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 |
| CN104691038B (en) * | 2013-12-06 | 2017-01-11 | 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 |
| CN104924704A (en) * | 2014-03-20 | 2015-09-23 | 中国科学院大连化学物理研究所 | High-temperature-resistant coating structure for steel structure surface and applications thereof |
| CN104924718A (en) * | 2014-03-20 | 2015-09-23 | 中国科学院大连化学物理研究所 | Metal surface high-temperature-resistant coating structure and applications thereof |
| CN104924718B (en) * | 2014-03-20 | 2017-01-25 | 中国科学院大连化学物理研究所 | Metal surface high-temperature-resistant coating structure and applications thereof |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130619 |
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| CX01 | Expiry of patent term |