CN204547235U - A kind of structure of rocket launching pad high temperature-resistant coating material - Google Patents

A kind of structure of rocket launching pad high temperature-resistant coating material Download PDF

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Publication number
CN204547235U
CN204547235U CN201520122337.XU CN201520122337U CN204547235U CN 204547235 U CN204547235 U CN 204547235U CN 201520122337 U CN201520122337 U CN 201520122337U CN 204547235 U CN204547235 U CN 204547235U
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organic
high temperature
coating material
resistant coating
top layer
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张巍
马磊
王国鹏
王晓东
张涛
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Dalian Institute of Chemical Physics of CAS
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Dalian Institute of Chemical Physics of CAS
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Abstract

The utility model discloses a kind of structure of rocket launching pad high temperature-resistant coating material, the structure of the utility model high temperature-resistant coating material is made up of organic underlayer, fire-resistant light aggregate and Organic-inorganic composite top layer, wherein, fire-resistant light aggregate is interspersed among organic underlayer and Organic-inorganic composite top layer.Organic underlayer is made up of epoxy resin, curing agent modified polyamine and flexibilizer liquid rubber, and Organic-inorganic composite top layer is made up of organic gel epoxy resin, polyurethane curing agent, sand and cement.High temperature-resistant coating material of the present utility model can bear rocket simulation gas-flow and wash away, and metal backing surface temperature is no more than 180 DEG C, and coating has good heat-proof quality.

Description

A kind of structure of rocket launching pad high temperature-resistant coating material
Technical field
The utility model relates to the structure of the high temperature-resistant coating material of rocket launching pad, especially relates to a kind of structure of high temperature-resistant coating material of the reduction rocket launching pad back of the body temperature for the coating of rocket launching pad surface, belongs to high temperature resistant adiabatic protection field.
Background technology
Along with the development of space flight, aerospace cause, high temperature-resistant coating material 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 rocket launching pad is coated with high temperature-resistant coating material; metal surface can be made heat insulation; reduce thermal ablation and thermal shock; and prevent rocket launching pad under the effect of repeatedly thermal shock load, producing heat fatigue, heat cracks and thermal destruction; thus guarantee the reliability of rocket launching pad work, extend the service life of rocket launching pad.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 it is thick that shortcoming is thickness, 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; this high temperature-resistant coating material not only serves the effect of protection rocket launching pad, also solves and all constructs by Inorganic Non-metallic Materials Heavy Weight, the irremovable problem that transmitting station causes.
Utility model content
Technical problem to be solved in the utility model increases thermal protection measure to ground installation rocket launching pad, and provide one can bear rocket wake flame and purge, metal backing temperature is no more than the high temperature-resistant coating material structure of 180 DEG C.
Technical problem to be solved in the utility model is achieved through the following technical solutions:
Set gradually organic bottom, fire-resistant light aggregate and Organic-inorganic composite top layer in substrate surface, wherein, fire-resistant light aggregate is interspersed among organic underlayer and Organic-inorganic composite top layer.
The thickness of described organic underlayer is 2 ~ 6mm;
Described substrate is embedded in organic underlayer for the fire-resistant light aggregate part described in metallic substrates, and a part is embedded in Organic-inorganic composite top layer, obtains " pinning " structure;
The thickness on described Organic-inorganic composite top layer is 3 ~ 14mm;
The gross thickness of described high temperature-resistant coating material structure is 5 ~ 20mm.
Count in mass ratio, organic underlayer is made up of epoxy resin 65 ~ 80%, curing agent modified polyamine 10 ~ 20%, flexibilizer liquid rubber 5 ~ 20%.
Described epoxy resin is one or more in 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 type epoxy resin, Hydromethyl bisphenol Resin, epoxide number scope 0.2-0.6.
Described curing agent modified polyamine is one or more in oneself two contracting amine of phenol formaldehyde (PF), phenol formaldehyde (PF) isophthalic two contracting amine, phenol formaldehyde (PF) second two contracting amine, metatitanic acid three isopropyl alcohol tertiary amine ester;
Described flexibilizer liquid rubber is one or more in dienes liquid rubber, alkenes liquid rubber, polyurethanes liquid rubber, liquid silastic, liquid polysulfide rubber, liquid fluorine rubber, and number-average molecular weight scope is 3000 ~ 6000.
The refractoriness of fire-resistant light aggregate is not less than 1200 DEG C, and the granularity of fire-resistant light aggregate is 6 ~ 35M.Al 2o 3content be preferably 10% ~ 55%.In the utility model, fire-resistant light aggregate is embedded in the middle of organic underlayer and Organic-inorganic composite top layer, two-layer connection can be made tightr, simultaneously, be can withstand high temperatures to the requirement of fire-resistant light aggregate, because aggregate is not exposed to surface, therefore to the requirement of aggregate for certain high temperature can be tolerated, preferred refractory temperature is for being not less than 1200 DEG C, simultaneously, consider the requirement of cost, fire-resistant light aggregate be preferable in haydites of book structure, leca, expanded perlite one or more, but this does not limit the selection to fire-resistant light aggregate.
Count in mass ratio, the composite that Organic-inorganic composite top layer is made up of organic gel epoxy resin, curing agent polyurethane, inorganic filler sand and cement, wherein, organic gel epoxy resin 40 ~ 60%, curing agent polyurethane 10 ~ 20%, sand 15 ~ 30%, cement 5 ~ 15%.
Organic gel epoxy resin is aqueous epoxy resins and the organic gel class identical with aqueous epoxy resins function.
Described polyurethane is polyurethanes.
The preparation method on Organic-inorganic composite top layer is:
By sand and cement according to (1.5 ~ 4.5): 1 mixes, obtain inorganic matter, by organic gel epoxy resin and polyurethane curing agent according to 3:(0.5 ~ 2) mixing, obtain organic matter, added to by inorganic matter in organic matter, inorganic matter and organic mass ratio are (0.8 ~ 4): 1.
The particle diameter of described sand is not more than 35 orders.
The beneficial effects of the utility model:
The structure that the utility model adopts is coated in successively on rocket launching pad in organic underlayer, fire-resistant light aggregate and Organic-inorganic composite top layer, when coating is subject to high temperature and the washing away at a high speed of gas-flow, first the Organic-inorganic composite top layer of coating material has a physics heat absorption sharply, and start chemical breakdown, temperature rises and internally conducts heat, residue after decomposition forms carbon residue layer, in top layer, high polymer is high by carbon forming rate after calcination, carbon residue layer is closely knit, possess the feature that ablation resistance is good, play heat-blocking action and resistance to erosion effect;
A described fire-resistant light aggregate part is embedded in organic underlayer, a part is embedded in Organic-inorganic composite top layer, utilize fire-resistant light aggregate this " pinning " structure, organic underlayer and Organic-inorganic composite top layer are better combined, increase the bonding on organic underlayer and Organic-inorganic composite top layer, in actual use, Organic-inorganic composite top layer difficult drop-off more.
The utility model will greatly reduce thermal ablation and the thermal shock of metallic matrix, and the back of the body temperature of metal will reduce greatly, and meanwhile, resistant to elevated temperatures utilization rate also increases, thus effectively plays thermal protection effect to rocket launching pad.
Accompanying drawing explanation
Fig. 1 is high temperature-resistant coating material structural representation, in figure: 1-steel plate 2-organic underlayer 3-fire-resistant light aggregate 4-Organic-inorganic composite top layer.
Detailed description of the invention
Following examples are used for the utility model is described in further detail, but do not form restriction of the present utility model, and concrete data of the present utility model are only limitted to absolutely not these embodiments.
Raw material is the material meeting professional standard, and the raw material that the utility model uses is not formed restriction of the present utility model.Cement: model is 425 portland cements, and manufacturer is Zhengzhou Dengfeng Smelting Materials Co., Ltd..Epoxy resin: model is SM828, curing agent modified polyamine: model is 703, 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.Fire-resistant light aggregate: granularity 6 ~ 35M, manufacturer is Zibo jewel kiln Materials Co., Ltd.
The preparation of embodiment 1 high temperature-resistant coating material
1. the preparation of organic underlayer: by epoxy resin, curing agent modified polyamine, flexibilizer liquid rubber according to after the mixing of 7:2:1 ratio, be coated on the steel plate of 190 × 120 × 5mm after rust cleaning, paint removal, coating thickness is 2mm.
2. fire-resistant light aggregate processing: after organic underlayer coating, be that the even spreading of fire-resistant light aggregate of 6 ~ 35M is pasted onto on organic underlayer at once by granularity.
3. the preparation on Organic-inorganic composite top layer: first filler sand and cement are mixed according to the ratio of 2:1, then add in organic gel epoxy resin and the epoxy glue of polyurethane curing agent according to 3:1 ratio, the ratio of solid and liquid is 3:1.
4. be evenly coated on fire-resistant light aggregate by Organic-inorganic composite top layer, coating thickness is 4mm, and preparation gross thickness is the high temperature-resistant coating material of 6mm.
As shown in Figure 1, a described fire-resistant light aggregate part is embedded in organic underlayer, and a part is embedded in Organic-inorganic composite top layer, forms " pinning " structure.
The thermal protection effect heat insulation to high temperature-resistant coating material 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 material, 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; The ablation test time: 2s/ part.Wake flame when experimental condition is rocket launching analog purges situation, and flame purges the metal foil scribbling high temperature-resistant coating material side.The back temperature of test metal foil.The metalwork back temperature measurement result of 6mm thick coating is as shown in table 1.As can be seen from the table, the back of the body Wen Wei of the sample of 6mm thick coating is applied more than 100 DEG C.Result of the test shows, high temperature-resistant coating material of the present invention and structure have good heat-proof quality, and protect metal substrate.
The metalwork back temperature measurement result of table 1 6mm thick coating
The preparation of embodiment 2 high temperature-resistant coating material
1. the preparation of organic underlayer: by epoxy resin, curing agent modified polyamine, flexibilizer liquid rubber according to after the mixing of 7:2:1 ratio, be coated on the steel plate of 190 × 120 × 5mm after rust cleaning, paint removal, coating thickness is 4mm.
2. fire-resistant light aggregate processing: after organic underlayer coating, be that the even spreading of fire-resistant light aggregate of 6 ~ 35M is pasted onto on organic underlayer at once by granularity.
3. the preparation on Organic-inorganic composite top layer: first filler sand and cement are mixed according to the ratio of 2:1, then add in organic gel epoxy resin and the epoxy glue of polyurethane curing agent according to 3:1 ratio, the ratio of solid and liquid is 3:1.
4. be evenly coated on fire-resistant light aggregate by Organic-inorganic composite top layer, coating thickness is 6mm, and preparation gross thickness is the high temperature-resistant coating material of 10mm.
As shown in Figure 1, a described fire-resistant light aggregate part is embedded in organic underlayer, and a part is embedded in Organic-inorganic composite top layer, forms " pinning " structure.
The thermal protection effect heat insulation to high temperature-resistant coating material 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 material, 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; The ablation test time: 2s/ part.Wake flame when experimental condition is rocket launching analog purges situation, and flame purges the metal foil scribbling high temperature-resistant coating material side.The back temperature of test metal foil.The metalwork back temperature measurement result of 10mm thick coating is as shown in table 2.As can be seen from the table, 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, high temperature-resistant coating material of the present invention and structure have good heat-proof quality, and protect metal substrate.
The metalwork back temperature measurement result of table 2 10mm thick coating

Claims (5)

1. the structure of a rocket launching pad high temperature-resistant coating material, it is characterized in that: set gradually organic bottom, fire-resistant light aggregate and Organic-inorganic composite top layer in substrate surface, wherein, a described fire-resistant light aggregate part is embedded in organic underlayer, and a part is embedded in Organic-inorganic composite top layer.
2. according to the structure of high temperature-resistant coating material according to claim 1, it is characterized in that: described organic underlayer thickness is 2 ~ 6mm.
3. according to the structure of high temperature-resistant coating material according to claim 1, it is characterized in that: the thickness on Organic-inorganic composite top layer is 3 ~ 14mm.
4., according to the structure of high temperature-resistant coating material according to claim 1, it is characterized in that:
The gross thickness of high temperature-resistant coating material structure is 5 ~ 20mm.
5. according to the structure of high temperature-resistant coating material according to claim 1, it is characterized in that: described substrate is metallic substrates.
CN201520122337.XU 2015-03-02 2015-03-02 A kind of structure of rocket launching pad high temperature-resistant coating material Active CN204547235U (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107081941A (en) * 2016-02-16 2017-08-22 中国科学院大连化学物理研究所 Structure and its application of a kind of metal surface with thermal protection coating material
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
CN107081939A (en) * 2016-02-16 2017-08-22 中国科学院大连化学物理研究所 A kind of rocket launching pad high-temperature resistant coating structure and its application

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107081941A (en) * 2016-02-16 2017-08-22 中国科学院大连化学物理研究所 Structure and its application of a kind of metal surface with thermal protection coating material
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
CN107081939A (en) * 2016-02-16 2017-08-22 中国科学院大连化学物理研究所 A kind of rocket launching pad high-temperature resistant coating structure and its application

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