CN103850355A - Structure for thermal protective coating of rocket launching pad and application thereof - Google Patents
Structure for thermal protective coating of rocket launching pad and application thereof Download PDFInfo
- Publication number
- CN103850355A CN103850355A CN201210514151.XA CN201210514151A CN103850355A CN 103850355 A CN103850355 A CN 103850355A CN 201210514151 A CN201210514151 A CN 201210514151A CN 103850355 A CN103850355 A CN 103850355A
- Authority
- CN
- China
- Prior art keywords
- organic
- thermal protection
- protection coating
- coating
- epoxy resin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A30/00—Adapting or protecting infrastructure or their operation
- Y02A30/24—Structural elements or technologies for improving thermal insulation
- Y02A30/244—Structural elements or technologies for improving thermal insulation using natural or recycled building materials, e.g. straw, wool, clay or used tires
Abstract
The invention discloses a structure for a thermal protective coating of a rocket launching pad and an application thereof. The thermal protective coating is composed of materials in three layers, namely, an organic bottom layer, refractory bricks and an organic-inorganic compound surface layer, wherein the organic bottom layer is composed of epoxy resin, solidifying agent polyamide and flexibilizer liquid rubber; clay refractory bricks are adopted as the refractory bricks; the organic-inorganic compound surface layer is composed of organic rubber epoxy resin, polyurethane curing agent, sand and cement. The material of the thermal protective coating provided by the invention can endure the scouring of the simulated fuel gas flow of a rocket; the temperature on a metal rear surface is not above 200 DEG C; the coating has an excellent heat-insulating property.
Description
Technical field
The present invention relates to the thermal protection coating structure of rocket launching pad, especially relate to a kind of reduction transmitting station applying for rocket launching pad surface and carry on the back warm thermal protection coating structure and application thereof, belong 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 is also increased to thermal protection measure as rocket launching pad.If transmitting station is coated with to thermal protection coating, can make 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 thermal shock load, thereby guarantee the reliability of transmitting station work, extend the application 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 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 cannot 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 to thermo-lag technology.
Summary of the invention
Technical problem to be solved by this invention is that ground installation rocket launching pad is increased to thermal protection measure, provides one can bear rocket wake flame and purges, and back of the body temperature is no more than the structure of the thermal protection coating of 200 ℃.
Technical problem to be solved by this invention is achieved through the following technical solutions:
Thermal protection coating structure of the present invention, is made up of trilaminate material, and bottom is organic material, and intermediate layer is refractory brick, and top layer is composite organic-inorganic material.
Bottom is made up of organic material, epoxy resin (mass ratio, lower same) 65 ~ 80%, curing compound polyamide 10 ~ 20%, flexibilizer liquid rubber 5 ~ 20%.The thickness of primer is 2 ~ 6mm.
Intermediate layer is made up of clay refractory brick, and its degree of fire resistance can reach 1730 ℃, Al
2o
3content > 40%.
The composite material that top layer is made up 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.
Thermal protection coating organic underlayer of the present invention, intermediate layer and organic and inorganic composite skins gross thickness are 10 ~ 35mm.
The present invention's raw material used can be bought and obtain from market, 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, curing compound 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.Organic gel epoxy resin: model is SM815, polyurethane curing agent: model is 735, and manufacturer is Sanmu Group Co., Ltd., Jiangsu.Refractory brick: model is (NZ)-2, and manufacturer is Zhonggang Group Refractory Material Co., Ltd..
When the present invention applies, organic underlayer, intermediate layer and organic and inorganic composite skins are coated on rocket launching pad successively, because the present invention adopts said structure, in the time that coating is subject to the high temperature of gas-flow and washing away at a high speed, first the skin-material of coating material has a physics heat absorption sharply, and start chemical breakdown, temperature rise to internal heat transfer.Residue after decomposition forms 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, carbon residue layer is closely knit is good.
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, thereby effectively rocket launching pad is played to thermal protection effect.
Accompanying drawing explanation
Fig. 1: the back temperature of 10mm coating sample and the relation curve of ablation time;
Fig. 2: the back temperature of 25mm coating sample and the relation curve of ablation time.
Fig. 3 is structural representation of the present invention.
Wherein, 1, substrate, 2, organic underlayer, 3, clay refractory brick layer, 4, 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 invention 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 compound polyamide 6 50, flexibilizer liquid rubber are mixed according to 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 in intermediate layer: the clay refractory brick that is 5mm by thickness (NZ)-2 sticks on organic underlayer.
3. the preparation of organic and inorganic composite skins: first filler sand and cement are mixed according to the ratio of 2:1, then add organic gel epoxy resin SM815 and polyurethane curing agent 735 to according in the epoxy glue of 3:1 ratio, the ratio of solid and liquid is 3:1.Skin-material is coated on refractory brick, and coating thickness is 3mm, the thermal protection coating that preparation gross thickness is 10mm.
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 to 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.Test conditions: engine combustion chamber pressure: Pc=1.4 ± 0.05MPa; Motor excess oxidizer coefficient: α=0.7 ± 0.03; Engine nozzle diameter: 65mm; The ablation test time: 5s/ part.Wake flame when test conditions is rocket launching analog purges situation, and flame purges the metal foil that scribbles thermal protection coating one side.The back temperature of test metal foil.The relation of the back temperature of 10mm 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 10mm thick coating exceedes 100 ℃.Result of the test shows, coating material of the present invention and structure have good heat-proof quality, and have protected steel plate ground.
The preparation of embodiment 2 thermal protection coating structures
1. the preparation of organic underlayer: after epoxy resin SM828, curing compound polyamide 6 50, flexibilizer liquid rubber are mixed according to 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 in intermediate layer: the clay refractory brick that is 15mm by thickness (NZ)-2 sticks on organic underlayer.
3. the preparation of organic and inorganic composite skins: first filler sand and cement are mixed according to the ratio of 2:1, then add organic gel epoxy resin SM815 and polyurethane curing agent 735 to according in the epoxy glue of 3:1 ratio, the ratio of solid and liquid is 3:1.Skin-material is coated on refractory brick, and coating thickness is 6mm, the thermal protection coating that preparation gross thickness is 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 to 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.Test conditions: engine combustion chamber pressure: Pc=1.4 ± 0.05MPa; Motor excess oxidizer coefficient: α=0.7 ± 0.03; Engine nozzle diameter: 65mm; The ablation test time: 5s/ part.Wake flame when test conditions is rocket launching analog purges situation, and flame purges the metal foil that scribbles thermal protection coating one side.The back temperature of test metal foil.The relation of the back temperature of 25mm 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 25mm thick coating exceedes 100 ℃.Result of the test shows, coating material of the present invention and structure have good heat-proof quality, and have protected steel plate ground.
Claims (10)
1. a structure for thermal protection coating for rocket launching pad, is characterized in that: be provided with successively organic underlayer (2), clay refractory brick layer (3) and organic and inorganic composite skins (4) trilaminate material composition in substrate (1) surface.
2. according to thermal protection coating claimed in claim 1, it is characterized in that: meter in mass ratio, organic underlayer is made up of epoxy resin 65 ~ 80%, curing compound polyamide 10 ~ 20%, flexibilizer liquid rubber 5 ~ 20%.
3. according to the structure of thermal protection coating claimed in claim 1, it is characterized in that: clay refractory brick degree of fire resistance can reach 1730 ℃, Al
2o
3content > 40%; The thickness of refractory brick is 5 ~ 15mm.
4. according to the structure of thermal protection coating claimed in claim 1, it is characterized in that: meter in mass ratio, organic and inorganic composite skins is the composite material by organic gel epoxy resin, polyurethane curing agent and inorganic filler sand and cement composition, wherein, organic gel epoxy resin 40 ~ 60%, polyurethane curing agent 10 ~ 20%, sand 15 ~ 30%, cement 5 ~ 15%.
5. according to the structure of thermal protection coating claimed in claim 2, it is characterized in that: organic underlayer thickness is 2 ~ 6mm.
6. according to the structure of thermal protection coating claimed in claim 4, it is characterized in that: the thickness of organic and inorganic composite skins material is 3 ~ 14mm.
7. according to the structure of thermal protection coating claimed in claim 1, it is characterized in that: thermal protection coating organic underlayer and organic and inorganic composite skins gross thickness are 10 ~ 35mm.
8. according to the structure of thermal protection coating claimed in claim 1, it is characterized in that: described substrate is metallic substrates.
9. according to the structure of thermal protection coating claimed in claim 4, it is characterized in that: described sand was component under the sieve after 35 mesh sieves.
Thermal protection coating described in claim 1-9 any one on rocket launching pad external surface as a thermal protection coating, be provided with successively organic underlayer, fire brick layer, organic and inorganic composite skins in transmitting station external surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210514151.XA CN103850355B (en) | 2012-12-04 | 2012-12-04 | The structure of a kind of rocket launching pad thermal protection coating and application thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210514151.XA CN103850355B (en) | 2012-12-04 | 2012-12-04 | The structure of a kind of rocket launching pad thermal protection coating and application thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103850355A true CN103850355A (en) | 2014-06-11 |
| CN103850355B CN103850355B (en) | 2016-08-03 |
Family
ID=50858465
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210514151.XA Active CN103850355B (en) | 2012-12-04 | 2012-12-04 | The structure of a kind of rocket launching pad thermal protection coating and application thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103850355B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105440814A (en) * | 2015-12-23 | 2016-03-30 | 巢湖诺信建材机械装备有限公司 | Bottom layer protective coating on air cannon nozzle |
| CN105984182A (en) * | 2015-03-02 | 2016-10-05 | 中国科学院大连化学物理研究所 | Thermal protection coating material structure for rocket launching pad and application of structure |
| CN105984183A (en) * | 2015-03-02 | 2016-10-05 | 中国科学院大连化学物理研究所 | High-temperature coating material structure for rocket launching pad and application of high-temperature coating material structure |
| CN116499309A (en) * | 2023-06-29 | 2023-07-28 | 北京坤飞航天科技有限公司 | Rocket launching pad heat protection structure and manufacturing method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0428531A (en) * | 1990-05-25 | 1992-01-31 | Sekiyu Kodan | Prepreg coating method using double-layer primer |
| CN1207058A (en) * | 1995-11-30 | 1999-02-03 | 阿迈隆国际公司 | Heat ablative coating composition |
| JP2004123779A (en) * | 2002-09-30 | 2004-04-22 | Dainippon Ink & Chem Inc | Epoxy resin composition and epoxy resin emulsion |
| CN1546590A (en) * | 2003-12-04 | 2004-11-17 | 四川大学 | Preparation method of room temperature cured high temperature tolerant flexible epoxy adhesive |
| CN1746236A (en) * | 2005-08-25 | 2006-03-15 | 复旦大学 | High-performance organic-inorganic resin coating material with hybrid acrylic ester and production thereof |
-
2012
- 2012-12-04 CN CN201210514151.XA patent/CN103850355B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0428531A (en) * | 1990-05-25 | 1992-01-31 | Sekiyu Kodan | Prepreg coating method using double-layer primer |
| CN1207058A (en) * | 1995-11-30 | 1999-02-03 | 阿迈隆国际公司 | Heat ablative coating composition |
| JP2004123779A (en) * | 2002-09-30 | 2004-04-22 | Dainippon Ink & Chem Inc | Epoxy resin composition and epoxy resin emulsion |
| CN1546590A (en) * | 2003-12-04 | 2004-11-17 | 四川大学 | Preparation method of room temperature cured high temperature tolerant flexible epoxy adhesive |
| CN1746236A (en) * | 2005-08-25 | 2006-03-15 | 复旦大学 | High-performance organic-inorganic resin coating material with hybrid acrylic ester and production thereof |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105984182A (en) * | 2015-03-02 | 2016-10-05 | 中国科学院大连化学物理研究所 | Thermal protection coating material structure for rocket launching pad and application of structure |
| CN105984183A (en) * | 2015-03-02 | 2016-10-05 | 中国科学院大连化学物理研究所 | High-temperature coating material structure for rocket launching pad and application of high-temperature coating material structure |
| CN105440814A (en) * | 2015-12-23 | 2016-03-30 | 巢湖诺信建材机械装备有限公司 | Bottom layer protective coating on air cannon nozzle |
| CN116499309A (en) * | 2023-06-29 | 2023-07-28 | 北京坤飞航天科技有限公司 | Rocket launching pad heat protection structure and manufacturing method |
| CN116499309B (en) * | 2023-06-29 | 2023-11-24 | 北京坤飞航天科技有限公司 | Rocket launching pad heat protection structure and manufacturing method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103850355B (en) | 2016-08-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203004461U (en) | Thermal protection coating structure for transmitting platform | |
| CN104691038B (en) | Structure of thermal protection coating used for steel structure surface and application thereof | |
| CN103847189B (en) | Structure and the application thereof of thermal protection coating for a kind of transmitting station | |
| CN103850355A (en) | Structure for thermal protective coating of rocket launching pad and application thereof | |
| CN109181390B (en) | A kind of heat-insulating, fire-preventing coating and its preparation process | |
| CN106433148B (en) | A kind of carbon cloth enhancing/resistance to ablative composite material of heat cure rubber and preparation method thereof | |
| CN107081941A (en) | Structure and its application of a kind of metal surface with thermal protection coating material | |
| CN203876314U (en) | High-temperature-resistant coating structure for steel structure surface | |
| CN204547235U (en) | A kind of structure of rocket launching pad high temperature-resistant coating material | |
| CN105291520B (en) | A kind of high-temperature resistant coating structure and its application on rocket launching pad | |
| CN204020133U (en) | The structure of high-temperaure coating for a kind of rocket launching pad | |
| CN105694082A (en) | Preparation method of high temperature resistant and corrosion resistant composite material | |
| CN104924718B (en) | Metal surface high-temperature-resistant coating structure and applications thereof | |
| NO784214L (en) | FIRE PROTECTIVE COATING SYSTEM AND ITS USE | |
| CN107652827B (en) | A kind of anti-insulating moulding coating and preparation method thereof | |
| CN203844362U (en) | Structure of high-temperature-resistant coating for metal surface | |
| CN209538438U (en) | A kind of fireproof coating composite construction for indoor thin section steel structure | |
| CN110373081B (en) | High-temperature-resistant powder coating structure and construction process thereof | |
| CN105088122B (en) | The Ni Al of Mg alloy surface2O3‑AlB12The preparation method of composite coating | |
| CN205601283U (en) | Metal surface is with structure of hot protective coating material | |
| CN106947368B (en) | A kind of resin ceramic material and preparation method thereof | |
| CN104924704A (en) | High-temperature-resistant coating structure for steel structure surface and applications thereof | |
| CN114605915A (en) | Heat-resistant ceramic coating, surface coating and preparation method | |
| CN205601268U (en) | Warship boat deck is with hot protective coating's structure | |
| CN104691065A (en) | Structure of thermal protection coating used for metal surface and application thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |