CN105984183A - High-temperature coating material structure for rocket launching pad and application of high-temperature coating material structure - Google Patents
High-temperature coating material structure for rocket launching pad and application of high-temperature coating material structure Download PDFInfo
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- CN105984183A CN105984183A CN201510095105.4A CN201510095105A CN105984183A CN 105984183 A CN105984183 A CN 105984183A CN 201510095105 A CN201510095105 A CN 201510095105A CN 105984183 A CN105984183 A CN 105984183A
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Abstract
The invention discloses a high-temperature coating material structure for a rocket launching pad and application of the high-temperature coating material structure. The high-temperature coating material structure is that an organic bottom layer, fire-resistant lightweight aggregates and an organic-inorganic compound surface layer are sequentially arranged on the surface of a launching pad base, wherein the fire-resistant lightweight aggregates penetrate through the organic bottom layer and the organic-inorganic compound surface layer. The organic bottom layer is prepared from epoxy resin, a curing agent modified polyamine and flexibilizer liquid rubber. The organic-inorganic combined surface layer is composed of organic glue epoxy resin, a polyurethane curing agent, sand and cement. The high-temperature coating material can bear scouring of rocket simulation combustion gas streams, the temperature of the metal back face does not exceed 180 DEG C, and the coating has good heat-shielding performance.
Description
Technical field
The present invention relates to the high temperature-resistant coating material structure of rocket launching pad, especially relate to a kind of for rocket
The high temperature-resistant coating material structure reducing rocket launching pad back of the body temperature of transmitting station surface coating and application thereof, belong to
High temperature resistant adiabatic protection field.
Background technology
With the development of space flight, aerospace cause, high temperature-resistant coating material has opened up new application.Except
Outside the thermal protection of aircraft itself, domestic thermal protection measure is too increased to ground installation such as rocket launching pad.
If rocket launching pad is coated with high temperature-resistant coating material, metal surface can be made heat insulation, reduce thermal ablation and heat
Impact, and it is disconnected to prevent rocket launching pad from producing heat fatigue, heat cracks and heat under the effect of repeatedly thermal shock load
Split, so that it is guaranteed that 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, this kind of by
It is better than organic ablation surface that ablation property is swept in the transmitting station fire-resistant air-blowing that Inorganic Non-metallic Materials is constructed, but shortcoming
That thickness is thick, Heavy Weight, and transmitting station cannot be carried out mobile.
Utilize special high temperature-resistant coating material and structure can carry out thermal protection to rocket launching pad, this resistance to
High temperature coating material not only serves the effect of protection rocket launching pad, also solves all by inorganic non-metallic
Heavy Weight, the irremovable problem that transmitting station causes constructed by material.
Content of the invention
The technical problem to be solved is to increase thermal protection measure to ground installation rocket launching pad, carries
Rocket wake flame purging, the high temperature-resistant coating material less than 180 DEG C for the metal backing temperature can be born for one.
The technical problem to be solved is achieved through the following technical solutions:
Set gradually organic bottom, fire-resistant light aggregate and Organic-inorganic composite top layer in substrate surface, its
In, fire-resistant light aggregate is interspersed among organic underlayer and Organic-inorganic composite top layer.
Count in mass ratio, organic underlayer by epoxy resin 65～80%, curing agent modified polyamine 10～20%,
Toughener liquid rubber 5～20% forms.
Described epoxy resin is bis-phenol A glycidyl ether type epoxy resin, bisphenol F epoxy resin, bis-phenol
S epoxy resin, halogenated bisphenol A epoxy resin, hydrogenated bisphenol A epoxy resin, bisphenol-A D-ring oxygen
One or more in resin, Hydromethyl bisphenol Resin, epoxide number scope 0.2-0.6.
Described curing agent modified polyamine is oneself two contracting amine, phenol formaldehyde (PF) isophthalic two contracting amine, benzene of phenol formaldehyde (PF)
One or more in phenol formaldehyde second two contracting amine, metatitanic acid three isopropanol tertiary amine ester；
Described toughener liquid rubber is dienes liquid rubber, alkenes liquid rubber, polyurethanes
One or more in liquid rubber, liquid silastic, liquid polysulfide rubber, liquid fluorine rubber, 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.
The content of Al2O3 is preferably 10%～55%.Fire-resistant light aggregate is embedded in organic underlayer and organic in the present invention
In the middle of-inorganic compounding top layer, the connection that can make two-layer is more tight, meanwhile, to fire-resistant light aggregate
Require as being resistant to high temperature, owing to aggregate is not exposed to surface, be therefore to tolerate to the requirement of aggregate
Certain high temperature, preferably refractory temperature are not less than 1200 DEG C, simultaneously, it is contemplated that the requirement of cost,
Fire-resistant light aggregate is preferable over haydites of book structure, leca, one or more in expanded perlite,
But this is not limiting as the selection to fire-resistant light aggregate.
Count in mass ratio, Organic-inorganic composite top layer be by organic gel epoxy resin, curing agent polyurethane,
Inorganic filler sand and the composite of cement composition, wherein, organic gel epoxy resin 40～60%, solidification
Agent polyurethane 10～20%, sand 15～30%, cement 5～15%.
Organic gel epoxy resin is aqueous epoxy resins and the organic gel identical with aqueous epoxy resins function
Class.
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, and obtains inorganic matter, by organic gel epoxy
Resin and polyurethane curing agent are according to 3:(0.5～2) mixing, obtain organic matter, adding inorganic matter to has
In machine thing, inorganic matter is (0.8～4) with the mass ratio of organic matter: 1.
The particle diameter of described sand is not more than 35 mesh.
The thickness of described organic underlayer is 2～6mm；
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.
Described substrate is metallic substrates.
Described high temperature-resistant coating material structure is used for rocket launching pad outer surface, depends in transmitting station outer surface
Secondary organic underlayer, fire-resistant light aggregate, Organic-inorganic composite top layer are set.
Beneficial effects of the present invention:
The structure that the present invention uses is to depend on organic underlayer, fire-resistant light aggregate and Organic-inorganic composite top layer
It secondary is coated on rocket launching pad, when coating is by the high temperature of combustion gas stream and when washing away of high speed, coating material
First the Organic-inorganic composite top layer of material has a physics heat absorption drastically, and starts chemical breakdown, temperature
Rising and internally conducting heat, the residue after decomposition forms carbon residue layer, and in top layer, high polymer is by carbon forming rate after calcination
Height, carbon residue layer are closely knit, possess the good feature of ablation resistance, play heat-blocking action and resistance to erosion effect；
A described fire-resistant light aggregate part is embedded in organic underlayer, and a part is embedded in organic and inorganic
In composite skins, utilize fire-resistant light aggregate this " pinning " structure, by organic underlayer and organic and inorganic
Composite skins is preferably combined together, and increases organic underlayer and the bonding on Organic-inorganic composite top layer,
In actual use, Organic-inorganic composite top layer more difficult drop-off.
To greatly reduce the thermal ablation of metallic matrix and thermal shock through the present invention, the back of the body temperature of metal will be significantly
Reducing, meanwhile, resistant to elevated temperatures utilization rate also increases, thus effectively play heat to rocket launching pad anti-
Protect effect.
Brief description
Fig. 1 is high temperature-resistant coating material structural representation, in figure: 1-steel plate 2-organic underlayer 3-is fire-resistant gently
Matter aggregate 4-Organic-inorganic composite top layer.
Detailed description of the invention
Following example are used for describing in further detail the present invention, but are not construed as limiting the invention, this
Bright concrete data are only limitted to absolutely not these embodiments.
Raw material is the material meeting professional standard, and the raw material that the present invention uses does not constitutes the limit to the present invention
System.Cement: model is 425 portland cements, manufacturer is Zhengzhou Dengfeng Smelting Materials Co., Ltd..Epoxy
Resin: model is SM828, curing agent modified polyamine: model is 703, manufacturer is that Wuxi is bright
Chemical Co., Ltd..Toughener liquid rubber: model is number-average molecular weight 4000, manufacturer is Dalian
Jinzhou 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: epoxy resin, curing agent modified polyamine, toughener liquid rubber are pressed
It after the mixing of 7:2:1 ratio, is coated on the steel plate of rust cleaning, 190 × 120 × 5mm after paint removal, painting
Covering thickness is 2mm.
2. fire-resistant light aggregate processing: after organic underlayer coating finishes, be 6～35M's by granularity at once
The uniform spreading of fire-resistant light aggregate is pasted onto on organic underlayer.
3. the preparation on Organic-inorganic composite top layer: first filler sand and cement are mixed according to the ratio of 2:1
Close uniformly, be then added in organic gel epoxy resin and the polyurethane curing agent epoxy glue according to 3:1 ratio,
Solid is 3:1 with the ratio of liquid.
4. being coated uniformly on fire-resistant light aggregate by Organic-inorganic composite top layer, coating thickness is 4mm,
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, part edge
It is embedded in Organic-inorganic composite top layer, form " pinning " structure.
The thermal protection effect that high temperature-resistant coating material on metal foil is heat insulation is tested:
YA6804 type oxygen kerosene engine is used to carry out the test of testpieces back temperature, sample to sample
Scribble high temperature-resistant coating material for metal foil side, be the back side without cated metal covering.Experimental condition:
Engine combustion chamber pressure: Pc=1.4 ± 0.05MPa；Engine excess oxidizer coefficient: α=0.7 ± 0.03；Send out
Motivation nozzle diameter: 65mm；The ablation test time: 2s/ part.When experimental condition is rocket launching analog
Wake flame purging situation, flame purging scribbles the metal foil of high temperature-resistant coating material side.Test metallic steel
The back temperature of plate.The metalwork back temperature measurement result of 6mm thick coating is as shown in table 1.From table
It can be seen that the back of the body temperature of the sample of coating 6mm thick coating is not less than 100 DEG C.Result of the test shows, this
The high temperature-resistant coating material of 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: epoxy resin, curing agent modified polyamine, toughener liquid rubber are pressed
It after the mixing of 7:2:1 ratio, is coated on the steel plate of rust cleaning, 190 × 120 × 5mm after paint removal, painting
Covering thickness is 4mm.
2. fire-resistant light aggregate processing: after organic underlayer coating finishes, be 6～35M's by granularity at once
The uniform spreading of fire-resistant light aggregate is pasted onto on organic underlayer.
3. the preparation on Organic-inorganic composite top layer: first filler sand and cement are mixed according to the ratio of 2:1
Close uniformly, be then added in organic gel epoxy resin and the polyurethane curing agent epoxy glue according to 3:1 ratio,
Solid is 3:1 with the ratio of liquid.
4. being coated uniformly on fire-resistant light aggregate by Organic-inorganic composite top layer, coating thickness is 6mm,
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, part edge
It is embedded in Organic-inorganic composite top layer, form " pinning " structure.
The thermal protection effect that high temperature-resistant coating material on metal foil is heat insulation is tested:
YA6804 type oxygen kerosene engine is used to carry out the test of testpieces back temperature, sample to sample
Scribble high temperature-resistant coating material for metal foil side, be the back side without cated metal covering.Experimental condition:
Engine combustion chamber pressure: Pc=1.4 ± 0.05MPa；Engine excess oxidizer coefficient: α=0.7 ± 0.03；Send out
Motivation nozzle diameter: 65mm；The ablation test time: 2s/ part.When experimental condition is rocket launching analog
Wake flame purging situation, flame purging scribbles the metal foil of high temperature-resistant coating material side.Test metallic steel
The back temperature of plate.The metalwork back temperature measurement result of 10mm thick coating is as shown in table 2.From table
It can be seen that the back of the body temperature of the sample of coating 10mm thick coating is not less than 100 DEG C.Result of the test shows,
The 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 (9)
1. a rocket launching pad high temperature-resistant coating material structure, it is characterised in that: depend in substrate surface
Secondary organic underlayer, fire-resistant light aggregate and Organic-inorganic composite top layer, wherein, fire-resistant light aggregate are set
It is interspersed among organic underlayer and Organic-inorganic composite top layer.
2. according to the high temperature-resistant coating material structure described in claim 1, it is characterised in that: in mass ratio
Meter, organic underlayer is by epoxy resin 65～80%, curing agent modified polyamine 10～20%, toughener liquid rubber
Glue 5～20% forms.
3. according to the high temperature-resistant coating material structure described in claim 1, it is characterised in that: fire-resistant light
The refractoriness of aggregate is not less than 1200 DEG C, and the granularity of fire-resistant light aggregate is 6～35M.
4. according to the high temperature-resistant coating material structure described in claim 1, it is characterised in that: in mass ratio
Meter, Organic-inorganic composite top layer is by organic gel epoxy resin, curing agent polyurethane, sand and cement group
Become, wherein, organic gel epoxy resin 40～60%, curing agent polyurethane 10～20%, sand 15～30%, water
Mud 5～15%.
5. according to the high temperature-resistant coating material structure described in claim 4, it is characterised in that:
The preparation method on Organic-inorganic composite top layer is:
By sand and cement according to (1.5～4.5): 1 mixes, and obtains inorganic matter, by organic gel ring
Epoxy resins and polyurethane curing agent are according to 3:(0.5～2) mixing, obtain organic matter, inorganic matter is added to
In organic matter, inorganic matter is (0.8～4) with the mass ratio of organic matter: 1.
6. according to the high temperature-resistant coating material structure described in claim 4 or 5, it is characterised in that:
The particle diameter of described sand is not more than 35 mesh.
7. according to the high temperature-resistant coating material structure described in claim 1, it is characterised in that:
The thickness of organic underlayer is 2～6mm；
The thickness on Organic-inorganic composite top layer is 3～14mm；
The gross thickness of high temperature-resistant coating material structure is 5～20mm.
8. according to the high temperature-resistant coating material structure described in claim 1, it is characterised in that: described substrate
For metallic substrates.
9. the high temperature-resistant coating material structure described in a claim 1-8 any one is used for rocket launching
On platform outer surface, set gradually organic bottom, fire-resistant light aggregate, organic and inorganic in transmitting station outer surface
Composite skins.
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| CN201510095105.4A CN105984183A (en) | 2015-03-02 | 2015-03-02 | High-temperature coating material structure for rocket launching pad and application of high-temperature coating material structure |
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Citations (5)
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| US6342272B1 (en) * | 2000-04-21 | 2002-01-29 | The United States Of America As Represented By The Secretary Of The Air Force | Multi-layer corrosion resistant coatings |
| CN101695954A (en) * | 2009-09-14 | 2010-04-21 | 辽宁渤海装饰材料有限公司 | Method for manufacturing armored fireproofing thermal baffle for ship |
| CN101792294A (en) * | 2010-03-30 | 2010-08-04 | 武汉钢铁(集团)公司 | Light thermal-shield refractory castable |
| CN103850355A (en) * | 2012-12-04 | 2014-06-11 | 中国科学院大连化学物理研究所 | Structure for thermal protective coating of rocket launching pad and application thereof |
| CN103880452A (en) * | 2014-03-31 | 2014-06-25 | 沈阳金安铸造材料有限公司 | Unshaped refractory material |
-
2015
- 2015-03-02 CN CN201510095105.4A patent/CN105984183A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6342272B1 (en) * | 2000-04-21 | 2002-01-29 | The United States Of America As Represented By The Secretary Of The Air Force | Multi-layer corrosion resistant coatings |
| CN101695954A (en) * | 2009-09-14 | 2010-04-21 | 辽宁渤海装饰材料有限公司 | Method for manufacturing armored fireproofing thermal baffle for ship |
| CN101792294A (en) * | 2010-03-30 | 2010-08-04 | 武汉钢铁(集团)公司 | Light thermal-shield refractory castable |
| CN103850355A (en) * | 2012-12-04 | 2014-06-11 | 中国科学院大连化学物理研究所 | Structure for thermal protective coating of rocket launching pad and application thereof |
| CN103880452A (en) * | 2014-03-31 | 2014-06-25 | 沈阳金安铸造材料有限公司 | Unshaped refractory material |
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