CN105984182A - Thermal protection coating material structure for rocket launching pad and application of structure - Google Patents
Thermal protection coating material structure for rocket launching pad and application of structure Download PDFInfo
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- CN105984182A CN105984182A CN201510093335.7A CN201510093335A CN105984182A CN 105984182 A CN105984182 A CN 105984182A CN 201510093335 A CN201510093335 A CN 201510093335A CN 105984182 A CN105984182 A CN 105984182A
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- thermal protection
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Abstract
The invention discloses a thermal protection coating material structure for a rocket launching pad and application of the structure. The thermal protection coating material is composed of a first organic layer, a refractory brick layer, a second organic layer and an unshaped refractory material layer, wherein the two organic layers are same in composition and are both composed of epoxy resin, curing agent modified polyamine and toughening agent liquid rubber, and the unshaped refractory material layer is composed of mullite, cordierite, aluminate cement and silica fume. The thermal protection coating material is high in adhesive force and can bear simulated combustion-gas flow scour of a rocket and greatly reduce thermal ablation and thermal shock of a metallic substrate; the thermal protection coating material has good high-temperature combustion-gas flow scour resistance and thermal insulating performance, the temperature of the back face of metal does not exceed 80 DEG C, and therefore an effective thermal protection effect on the rocket launching pad is achieved.
Description
Technical field
The invention belongs to high temperature resistant adiabatic protection field, be specifically related to a kind of rocket launching pad thermal protection coating
Material structure and application thereof.
Background technology
Along with space flight, the development of aerospace cause, the new application of thermal protection coating materials open.Except
Outside the thermal protection of aircraft itself, domestic ground installation such as rocket launching pad is too increased thermal protection measure.
If rocket launching pad is coated with thermal protection 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 exhaustion, 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 transmitting station.Abroad, Europe
It is concrete flat pad that continent space agency is positioned at the Ariane rocket flat pad in Guyana, South America, this kind of by nothing
It is better than organic ablation surface that ablation property is swept in the transmitting station fire-resistant air-blowing that machine nonmetallic materials are constructed, but shortcoming is
Thickness is thick, Heavy Weight, and transmitting station cannot be carried out mobile.
Utilizing special thermal protection coating material that rocket launching pad can carry out thermal protection, this thermal protection is coated with
Layer material not only serves the effect of protection rocket launching pad, also solves all by Inorganic Non-metallic Materials structure
Build Heavy Weight, irremovable problem that transmitting station causes.
Summary of the invention
The technical problem to be solved is that ground installation rocket launching pad is increased thermal protection measure, carries
Rocket wake flame purging, the structure of the back of the body temperature thermal protection coating material less than 80 DEG C can be born for one.
The technical problem to be solved is achieved through the following technical solutions:
A kind of rocket launching pad thermal protection coating material structure, sets gradually in rocket launching pad substrate surface
Organic layer, fire brick layer, organic layer and unshape refractory layer four layer material.
Count in mass ratio, organic layer by epoxy resin 65～80%, curing agent modified polyamine 10～20%, increase
Tough dose of liquid rubber 5～20% composition.
Described epoxy resin is 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-ring oxygen tree
One or more in fat, 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, phenol of phenol formaldehyde (PF)
One or more in formaldehyde second two contracting amine, metatitanic acid three isopropanol tertiary amine ester；
Described toughener liquid rubber is dienes liquid rubber, alkenes liquid rubber, polyurethanes liquid
One or more in body rubber, liquid silastic, liquid polysulfide rubber, liquid fluorine rubber, number is all
Molecular weight is 3000～6000.
The refractoriness of described fire brick layer is not less than 1580 DEG C, and in refractory brick, Al2O3 content is 40%～47%.
Unshape refractory layer is made up of mullite, cordierite, aluminate cement and silicon ash, wherein,
Count in mass ratio, mullite 40～70%, cordierite 5～25%, aluminate cement 10～30%, silicon ash 2～10%.
Described fire brick layer is schamotte brick layer.
Organic layer thickness is 2～6mm；
The thickness of fire brick layer is 5～15mm；
Unshape refractory layer thickness is 6～14mm；
Thermal protection coating material structure gross thickness is 15～40mm.
Described substrate is metallic substrates.
Described mullite granularity is 5-3mm and 3-1mm, and cordierite granularity is 0.5-1mm.
Described thermal protection coating material structure is applied to as thermal protection coating material on transmitting station outer surface,
Organic layer, fire brick layer, organic layer and unshape refractory layer is set gradually in transmitting station outer surface.
Two-layer organic layer composition is identical, is formed by organic material, epoxy resin (mass ratio, lower same)
65～80%, curing agent modified polyamine 10～20%, toughener liquid rubber 5～20%.The thickness of organic layer is
2～6mm.
Unshape refractory layer is made up of inorganic material, mullite 40～70%, cordierite 5～25%, aluminum
Acid salt cement 10～30%, silicon ash 2～10%, the thickness of unshape refractory layer is 6～14mm.
The preparation method of unshape refractory layer is: first by the mullite of 5-3mm and 3-1mm according to
1:(0.8～2) mass ratio mix homogeneously, the most again by mixed mullite and cordierite, aluminic acid
Salt cement, silicon ash is according to mass ratio 11:(4～8): (2～8): (0.5～2) mix.To be mixed uniformly
After, the stirring that adds water (2～6) min, amount of water is (11～15) % of unshape refractory layer dosage
(mass fraction).
The organic layer of thermal protection coating material of the present invention, fire brick layer, organic layer and unshape refractory layer
Gross thickness is 15～40mm.
The invention have the benefit that
The thermal protection coating material cohesion of the present invention is strong, it is possible to bear rocket simulation combustion airflow scouring, metal
Back temperature is less than 80 DEG C, and thermal protection coating material has good heat-proof quality.
When the present invention applies, organic layer, fire brick layer, organic layer and unshape refractory layer are coated with successively
Overlay on rocket launching pad.Owing to four layer materials of the present invention containing fire brick layer and unshape refractory
Layer, two-layer is formed by Inorganic Non-metallic Materials, and therefore the refractoriness of coating material is high, and intensity is big.Work as fire
When arrow launches, coating is by the high temperature of combustion gas stream and washing away at a high speed, and coating is outermost unsetting
Refractory masses is capable of withstanding ablation and resistance to erosion, serves heat-blocking action, therefore protects rocket launching pad.
As can be seen here, thermal ablation and the thermal shock of metallic substrates, the back of the body of metal will be greatly reduced through the present invention
Temperature will be substantially reduced, thus rocket launching pad plays thermal protection effect effectively.
Accompanying drawing explanation
Fig. 1: thermal protection coating material structure schematic diagram；
In figure: 1-steel plate, 2-organic layer, 3-fire brick layer, 4-unshape refractory 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 industry standard, and the raw material that the present invention uses does not constitutes the limit to the present invention
System.The raw material that the present invention uses is: toughener liquid rubber: model is number-average molecular weight 4000, produces
Producer is Jinzhou Dalian Sheng Da product of rubber and plastic company limited.Refractory brick: model is (NZ)-2, manufacturer
It it is Zhonggang Group Refractory Material Co., Ltd..Aluminate cement: model is Secar71, manufacturer is triumphant
Northey (Chinese) aluminate Technology Co., Ltd..Mullite: granularity 5-3mm and 3-1mm, factory
Family is Jing Zhouhua prosperous mullite company limited.Cordierite: granularity 0.5-1mm, Yanshi City of manufacturer is bright
High-tech fire resistive material product company limited.Silicon ash: model 970, manufacturer is sky, Shanghai happy silica flour material
Company limited.
The preparation of embodiment 1 thermal protection coating material
As shown in Figure 1:
1. the preparation of ground floor organic layer: by epoxy resin, curing agent modified polyamine, toughener liquid
After rubber mixes according to 7:2:1 mass ratio, it is coated in the steel plate one of 190 × 120 × 5mm after rust cleaning
On side surface, coating thickness is 2mm.
2. the preparation of fire brick layer: clay refractory brick (NZ)-2 that thickness is 5mm has been placed on
On machine layer so that clay refractory brick layer is fitted with organic layer, is fixed on steel plate by fire brick layer.
3. the preparation of second layer organic layer: by epoxy resin, curing agent modified polyamine, toughener liquid
After rubber mixes according to 7:2:1 mass ratio, being coated on clay refractory brick layer, coating thickness is 2mm.
4. the preparation of unshape refractory layer: first by the mullite of 5-3mm and 3-1mm according to 1:1
Mass ratio mix homogeneously, the most again by mixed mullite and cordierite, aluminate cement, silicon ash
Mix according to mass ratio 11:5:4:1.To be mixed uniformly after, add water stirring 3min, and amount of water is indefinite
13% (mass fraction) of shape refractory masses dosage.Second layer organic layer coats is in clay refractory brick
After Ceng, it is not necessary to wait, unshape refractory can be coated on second layer organic layer, unsetting resistance to
The coating thickness of fire material layer is 6mm, and preparation gross thickness is the thermal protection coating material of 15mm.
The thermal protection effect that thermal protection coating material structure on metal foil is heat insulation is tested:
Use YA6804 type oxygen kerosene engine that sample carries out the test of testpieces back temperature, sample
Scribble thermal protection 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；Electromotor excess oxidizer coefficient: α=0.7 ± 0.03；Send out
Motivation nozzle diameter: 65mm；Nozzle exit fuel gas temperature: 2210K；Nozzle exit combustion gas speed: 2390
m/s；Chamber temperature: 3470K；The ablation test time: 5s/ part；Heat flow density: 17.9Mw/m2。
Experimental condition is wake flame purging situation during rocket launching analog, and flame purging scribbles thermal protection coating material one
The metal foil of side.Test metal is without the temperature (back temperature) of coating side.15mm thick coating
Metalwork back temperature measurement result as shown in table 1.As can be seen from the table, coating 15mm thick coating
The back of the body temperature of sample not less than 80 DEG C.Result of the test shows, the thermal protection coating material of the present invention and structure
Adhesive force is strong, has good heat-proof quality, and protects metallic substrates.
The back temperature measurement result of table 1 15mm thermal protection coating material sample
The preparation of embodiment 2 thermal protection coating material structure
1. the preparation of ground floor organic layer: by epoxy resin, curing agent modified polyamine, toughener liquid rubber
After glue mixes according to 7:2:1 mass ratio, it is coated in the steel plate side of 190 × 120 × 5mm after rust cleaning
On surface, coating thickness is 4mm.
2. the preparation of fire brick layer: clay refractory brick (NZ)-2 that thickness is 15mm has been placed on
On machine layer so that clay refractory brick layer is fitted with organic layer, is fixed on steel plate by fire brick layer.
3. the preparation of second layer organic layer: by epoxy resin, curing agent modified polyamine, toughener liquid
After rubber mixes according to 7:2:1 mass ratio, being coated on clay refractory brick, coating thickness is 2mm.
4. the preparation of unshape refractory layer: first by the mullite of 5-3mm and 3-1mm according to 1:1
Mass ratio mix homogeneously, the most again by mixed mullite and cordierite, aluminate cement, silicon ash
Mix according to mass ratio 11:5:4:1.To be mixed uniformly after, add water stirring 3min, and amount of water is top layer
13% (mass fraction) of dosage.Second layer organic layer coats is after clay refractory brick layer, it is not necessary to etc.
Treat, unshape refractory can be coated on second layer organic layer, the painting of unshape refractory layer
Covering thickness is 9mm, and preparation gross thickness is the high-temperaure coating of 30mm.
The thermal protection effect that thermal protection coating material on metal foil is heat insulation is tested:
Use YA6804 type oxygen kerosene engine that sample carries out the test of testpieces back temperature, sample
Scribble high-temperature resistant coating for metal foil side, be the back side without cated metal covering.Experimental condition: send out
Motivation chamber pressure: Pc=1.4 ± 0.05MPa；Electromotor excess oxidizer coefficient: α=0.7 ± 0.03；Start
Machine nozzle diameter: 65mm；Nozzle exit fuel gas temperature: 2210K；Nozzle exit combustion gas speed: 2390m/s；
Chamber temperature: 3470K；The ablation test time: 10s/ part；Heat flow density: 17.9Mw/m2.Test
Condition is wake flame purging situation during rocket launching analog, and flame purging scribbles thermal protection coating material side
Metal foil.Test metal is without the temperature (back temperature) of coating side.The gold of 30mm thick coating
Belong to part back temperature measurement result as shown in table 2.As can be seen from the table, the examination of 30mm thick coating is coated
The back of the body temperature of sample is not less than 80 DEG C.Result of the test shows, the coating material of the present invention is strong with structure adhesive force,
There is good heat-proof quality, and protect metallic substrates.
The back temperature measurement result of table 2 30mm thermal protection coating material sample
Claims (10)
1. a rocket launching pad thermal protection coating material structure, it is characterised in that: in rocket launching pad
Substrate surface sets gradually organic layer, fire brick layer, organic layer and unshape refractory layer four layer material.
2. according to the thermal protection coating material structure described in claim 1, it is characterised in that: in mass ratio
Meter, organic layer is by epoxy resin 65～80%, curing agent modified polyamine 10～20%, toughener liquid rubber
5～20% form.
3. according to the thermal protection coating material structure described in claim 2, it is characterised in that: toughener liquid
Body rubber is dienes liquid rubber, alkenes liquid rubber, polyurethanes liquid rubber, liquid silicon rubber
One or more in glue, liquid polysulfide rubber, liquid fluorine rubber.
4. according to the thermal protection coating material structure described in claim 1, it is characterised in that: described is resistance to
The refractoriness of firebrick layer is not less than 1580 DEG C, Al in refractory brick2O3Content is 40%～47%.
5. according to the thermal protection coating material structure described in claim 1, it is characterised in that: unsetting resistance to
Fire material layer is made up of mullite, cordierite, aluminate cement and silicon ash, wherein, counts in mass ratio,
Mullite 40～70%, cordierite 5～25%, aluminate cement 10～30%, silicon ash 2～10%.
6. according to the thermal protection coating material structure described in claim 1, it is characterised in that:
Described fire brick layer is schamotte brick layer.
7. according to the thermal protection coating material structure described in claim 1, it is characterised in that:
Organic layer thickness is 2～6mm；
The thickness of fire brick layer is 5～15mm；
Unshape refractory layer thickness is 6～14mm；
Thermal protection coating material structure gross thickness is 15～40mm.
8. according to the thermal protection coating material structure described in claim 1, it is characterised in that: described substrate
For metallic substrates.
9. according to the thermal protection coating material structure described in claim 5, it is characterised in that: described do not come
Stone granularity is 5-3mm and 3-1mm, and cordierite granularity is 0.5-1mm.
10. the thermal protection coating material structure described in a claim 1-9 any one is used for transmitting station
As thermal protection coating material on outer surface, in transmitting station outer surface set gradually organic layer, fire brick layer,
Organic layer and unshape refractory layer.
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| CN201510093335.7A CN105984182A (en) | 2015-03-02 | 2015-03-02 | Thermal protection coating material structure for rocket launching pad and application of structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109824932A (en) * | 2018-12-31 | 2019-05-31 | 合肥乐凯科技产业有限公司 | A kind of that resist warping optics basement membrane |
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| 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 |
| CN203876314U (en) * | 2014-03-20 | 2014-10-15 | 中国科学院大连化学物理研究所 | High-temperature-resistant coating structure for steel structure surface |
| CN204020133U (en) * | 2014-07-01 | 2014-12-17 | 中国科学院大连化学物理研究所 | The structure of high-temperaure coating for a kind of rocket launching pad |
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2015
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Patent Citations (4)
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| 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 |
| 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 |
| CN203876314U (en) * | 2014-03-20 | 2014-10-15 | 中国科学院大连化学物理研究所 | High-temperature-resistant coating structure for steel structure surface |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109824932A (en) * | 2018-12-31 | 2019-05-31 | 合肥乐凯科技产业有限公司 | A kind of that resist warping optics basement membrane |
| CN109824932B (en) * | 2018-12-31 | 2021-08-27 | 合肥乐凯科技产业有限公司 | Anti-warping optical base film |
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Application publication date: 20161005 |