CN203628151U - High-temperature-resistant integral rigid thermal insulation component - Google Patents
High-temperature-resistant integral rigid thermal insulation component Download PDFInfo
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- CN203628151U CN203628151U CN201320526457.7U CN201320526457U CN203628151U CN 203628151 U CN203628151 U CN 203628151U CN 201320526457 U CN201320526457 U CN 201320526457U CN 203628151 U CN203628151 U CN 203628151U
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Abstract
The utility model relates to a high-temperature-resistant integral rigid thermal insulation component which comprises a rigid fiber thermal insulation layer, an aerogel permeating layer permeating into the rigid fiber thermal insulation layer and a fiber fabric panel reinforcing layer disposed on at least one side of the rigid fiber thermal insulating layer. The high-temperature-resistant integral rigid thermal insulation component is high in strength, good in thermal insulation performance and excellent in anti-scouring performance, and can be used as outer thermal insulation materials.
Description
Technical field
The utility model relates to a kind of rigidity heat insulating component and preparation method thereof, particularly relates to a kind of high temperature resistant integrative rigidity heat insulating component and preparation method thereof, belongs to technical field of composite materials.
Background technique
Thermal protection system is in Aerodynamic Heating environment, to exempt from and burn and overheated structure for guard space aircraft, is mainly divided into ablating heat shield system and reusable thermal protection system.Reusable thermal protection system is to reuse the world its very crucial system of round transporting, and mainly contains at present ceramic tile formula thermal protection system and cover-plate type combination thermal protection system.Although ceramic insulation is watt high temperature resistant, because of the physics fragility of himself, once has the record repeatedly coming off in the process of space shuttle rise and fall, this makes the emphasis that people study start to turn to more complicated cover-plate type combination thermal protection system.
So-called cover-plate type combination thermal protection system, is combined into element of construction by cover plate materials and thermal-protective material according to certain mode, is fixed on airframe structure, plays the effect of carrying and solar heat protection.Compared with ceramic insulation tile, its superiority is mainly manifested in can resistance to higher temperature, be easy to the aspects such as installation and removal, shock resistance enhancing, and the fuselage of X-33 has adopted this heat insulation mode.
The difference of press cover sheet material matter, cover-plate type thermal protection system is divided into metal cover board thermal protection system and the board-like thermal protection system of ceramic cap.Intensity that metal cover board thermal protection system has overcome ceramic tile is low, property is crisp and a series of shortcoming such as easy water suction, and the intensity that it is higher and toughness make it more to demonstrate high integrity and the reusability of structure in rugged environment.But, the overheated ability of metal cover board, thermal expansion distortion arching causes boundary layer to change turbulent flow into from laminar flow prematurely, and design and manufacturing process complexity, is difficult to test and quality monitoring.The thermal expansion coefficient of metal is large, in the time that it suffers large temperature gradient, thermal stress fatigue likely occurs and destroy.The intensity of ceramic cover plate is not as metal cover board, but good hot operation ability, high thermal-shock resistance and longer operating life, make it to become a kind of more advanced composite material that improves thermal protection struc ture and performance thereof, be a kind of desirable cover plate materials, thereby solar heat protection still depend on the board-like thermal protection system of ceramic cap on a large scale.
At present, cover-plate type thermal protection system is all that cover plate materials and thermal-protective material are prepared respectively, adopt machinery type to link into an integrated entity, such combination easily makes thermal protection system that the damage of following several respects occurs again: the damage of loosening, the shock of loosening, the panel of frame bottom, serious plate.This is mainly due to the reason of cover plate and the combination of thermal-protective material later stage, and cover plate and thermal-protective material integrated molding will overcome the above problems.
Model utility content
The purpose of this utility model is to overcome the deficiency that the board-like thermal protection system preparation technology of existing ceramic cap causes its performance deficiency, and a kind of high temperature resistant integrative rigidity heat insulating component is provided.
The purpose of this utility model is achieved by the following technical solution:
1, a high temperature resistant integrative rigidity heat insulating component, is characterized in that, described high temperature resistant integrative rigidity heat insulating component comprises:
Rigid fiber thermal-protective coating;
Infiltrate into the aerogel permeable formation in described rigid fiber thermal-protective coating;
Fabric panel enhancement layer at least one side of described rigid fiber thermal-protective coating.
2, the high temperature resistant integrative rigidity heat insulating component as described in technological scheme 1, is characterized in that, described high temperature resistant integrative rigidity heat insulating component comprises:
Fabric panel enhancement layer on the both sides of described rigid fiber thermal-protective coating.
3. the high temperature resistant integrative rigidity heat insulating component as described in technological scheme 1 or 2, is characterized in that, has the outside of the described rigid fiber thermal-protective coating of aerogel permeable formation also to comprise impervious barrier in infiltration.
4. the high temperature resistant integrative rigidity heat insulating component as described in technological scheme 1 or 2, is characterized in that, the stitching fibre threads identical with fabric panel enhancement layer by material is sewed together described rigid fiber thermal-protective coating and described fabric panel enhancement layer.
5, the high temperature resistant integrative rigidity heat insulating component as described in technological scheme 4, is characterized in that, the needle gage of making is 10mm to 20mm, and the line-spacing of sewing line is 10mm to 20mm.
6, the high temperature resistant integrative rigidity heat insulating component as described in technological scheme 4, is characterized in that, described high temperature resistant integrative rigidity heat insulating component also permeates and has ceramic forerunner permeable formation.
7, the high temperature resistant integrative rigidity heat insulating component as described in technological scheme 5, is characterized in that, described high temperature resistant integrative rigidity heat insulating component also permeates and has ceramic forerunner permeable formation.
8, a method of preparing high temperature resistant integrative rigidity heat insulating component, is characterized in that, described method comprises the steps:
(1) preparation of rigidity aerogel composite: adopt rigid fiber goods as fibre reinforcement, described fibre reinforcement and aerogel precursor liquid solution are undertaken compound by sol-gel, aging, solvent exchange and supercritical drying process, obtain rigidity aerogel composite;
(2) the antiseepage processing of thermal-protective coating: adopt antiseepage primer to soak described rigidity aerogel composite, then in oven dry, so that antiseepage processing is carried out in the surface of described rigidity aerogel composite, thereby obtain thermal-protective coating;
(3) panel reinforcement and thermal-protective coating is compound: adopt fabric as panel reinforcement, described panel reinforcement and described thermal-protective coating are fixed together, then adopt draw point and sew up fibre threads and sew up, obtaining panel reinforcement-thermal-protective coating and make structure;
(4) preparation of ceramic-base panel material: panel reinforcement-thermal-protective coating that step (3) is obtained is made structure and is placed in target profile frock, use ceramic forerunner to flood described panel reinforcement-thermal-protective coating and make structure, then dry, sintering, makes the described high temperature resistant integrative rigidity heat insulating component with ceramic-base panel material.
9, the method as described in technological scheme 8, is characterized in that, carries out described dipping by vacuum hammering method.
10, according to the method described in technological scheme 8 or 9, it is characterized in that, the rigid fiber goods in described step (1) are ceramic fiber watt.
11, according to the method described in technological scheme 10, it is characterized in that, described ceramic fiber watt is made by the ceramic fiber of the group of selecting free mullite fiber, aluminum silicate fiber, quartz fibre and alumina fibre to form.
12, according to the method described in any one in technological scheme 8 to 11, it is characterized in that, described aerogel precursor liquid solution selects the group of free ethyl orthosilicate, methyl silicate, water glass, Ludox and multi-polysiloxane composition.
13, according to the method described in any one in technological scheme 8 to 12, it is characterized in that, the antiseepage primer in described step (2) selects the group of free trim,ethylchlorosilane, silazane, MTMS and hexamethyldisilane composition.
14, according to the method described in any one in technological scheme 8 to 13, it is characterized in that, the fabric in described step (3) selects the group of the fabric composition of free quartz fibre, alumina silicate, mullite fiber, alumina fibre, Zirconium oxide fibre.
15, according to the method described in any one in technological scheme 8 to 14, it is characterized in that, the material of described stitching fibre threads is identical with the fiber in fabric; Preferably, the needle gage of making is 10mm to 20mm, and the line-spacing of sewing line is 10mm to 20mm.
16, according to the method described in any one in technological scheme 8 to 14, it is characterized in that, the ceramic forerunner in described step (4) is Ludox and/or aluminium colloidal sol.
17, the high temperature resistant integrative rigidity heat insulating component being made by the method described in any one in technological scheme 8 to 16.
The utility model beneficial effect compared with prior art:
The utility model is not changing under the prerequisite of aerogel composite heat-shielding performance and panel mechanical property, by panel and insulating layer material combine closely, integrated molding, prepare high temperature resistant integrative rigidity heat insulating component, significantly improve the defect of the board-like thermal protection system easy damaged of original ceramic cap, be conducive to this thermal protection system widespread adoption.
accompanying drawing explanation
Fig. 1 is the utility model process flow diagram.
Fig. 2 is the schematic diagram of the high temperature resistant integrative rigidity heat insulating component of a mode of execution of the present utility model.
embodiment
As mentioned above, the utility model provides a kind of high temperature resistant integrative rigidity heat insulating component and preparation method thereof.
In first aspect of the present utility model, a kind of high temperature resistant integrative rigidity heat insulating component is provided, described high temperature resistant integrative rigidity heat insulating component comprises:
Rigid fiber thermal-protective coating;
Infiltrate into the aerogel permeable formation in described rigid fiber thermal-protective coating;
Fabric panel enhancement layer at least one side of described rigid fiber thermal-protective coating.
In some embodiments, in the both sides of described high temperature resistant integrative rigidity heat insulating component, fabric panel enhancement layer is set.
As shown in Figure 2, have in infiltration on the both sides of rigid fiber thermal-protective coating 2 of aerogel permeable formation, be sewed with fabric panel enhancement layer 1 by fiber stitching thread 3.
In some embodiments, rigid fiber can be ceramic fiber watt.In some embodiments, described ceramic fiber watt is made by the ceramic fiber of the group of selecting free mullite fiber, aluminum silicate fiber, quartz fibre and alumina fibre to form.
In some embodiments, fabric selects the group of the fabric composition of free quartz fibre, alumina silicate, mullite fiber, alumina fibre, Zirconium oxide fibre.
In some embodiments, described aerogel permeable formation can be by making precursor solution, for example select the precursor solution of the group of free ethyl orthosilicate, methyl silicate, water glass, Ludox and multi-polysiloxane composition, flood described rigid fiber thermal-protective coating, and then by sol-gel, aging, solvent exchange and supercritical drying
Dry process makes the precursor solution of infiltration in rigid fiber thermal-protective coating form described aerogel permeable formation.
In some embodiments, described rigid fiber thermal-protective coating and described fabric panel enhancement layer are sewed together, so that they are bonded to each other more securely.The sewing line of making employing is preferably the stitching fibre threads that material is identical with fabric panel enhancement layer.The advantage of doing is like this, changes while using described high temperature resistant integrative rigid member in rugged environment greatly in temperature environment, is unlikely to cause the combination between them to get loose because expand with heat and contract with cold; And, surprisingly, adopt the material stitching fibre threads identical with fabric panel enhancement layer to sew up, can significantly improve the heat-shielding performance of high temperature resistant integrative rigidity heat insulating component.In some embodiments preferably, the needle gage of making is 10mm to 20mm, for example, be 10mm, 12mm, 14mm, 16mm, 18mm or 20mm.In addition in some embodiments preferably, the line-spacing of sewing line is 10mm to 20mm, for example, be 10mm, 12mm, 14mm, 16mm, 18mm or 20mm.The utility model people finds, while use in hot environment, if needle gage or line-spacing are excessive, the combination dynamics between each layer of described high temperature resistant integrative rigid member is less, if needle gage or line-spacing are too small, likely make described high temperature resistant integrative rigid member rupture along sewing line, and affect its heat-shielding performance.
In some embodiments, there is the outside of the described rigid fiber thermal-protective coating of described aerogel permeable formation also to comprise the impervious barrier being formed by antiseepage primer in infiltration, to prevent that the material outside rigid fiber thermal-protective material and aerogel material from penetrating in described rigid fiber thermal-protective coating, thereby cause the thermal conductivity of described rigid fiber thermal-protective coating to increase, deterioration of thermal insulation performance.
In some embodiments, described antiseepage primer selects the group of free trim,ethylchlorosilane, silazane, MTMS and hexamethyldisilane composition.
In some embodiments, described high temperature resistant integrative rigidity heat insulating component also permeates and has ceramic forerunner permeable formation.In some embodiments, described ceramic forerunner is Ludox and/or aluminium colloidal sol.
In second aspect of the present utility model, a kind of method of preparing high temperature resistant integrative rigidity heat insulating component is provided, described method comprises:
(1) provide rigid fiber layer;
(2) rigid fiber layer described in use aerogel precursor body sol impregnation;
(3) make the aerogel precursor body collosol and gel in described rigid fiber layer and be dried, thereby obtaining rigid fiber thermal-protective coating; With
(4) at least one side of described rigid fiber thermal-protective coating, fabric panel enhancement layer is set.
In some embodiments, by the mode of making, described rigid fiber thermal-protective coating and described fabric panel enhancement layer are sewed together.
Some preferred embodiment in, also have the outside of the described rigid fiber thermal-protective coating of aerogel permeable formation also to comprise impervious barrier in infiltration.
Some preferred embodiment in, after making, be also immersed in ceramic forerunner making the high temperature resistant integrative rigid member obtaining, dry and sintering, forms ceramic forerunner permeable formation.
With reference to figure 1, the method for preparing described high temperature resistant integrative rigidity heat insulating component comprises:
Preparation rigidity aerogel composite; Thermal-protective coating antiseepage processing; Panel reinforcement and thermal-protective coating are sewed up; And prepare four steps such as ceramic-base panel material.
For example, some preferred embodiment in, described method comprises the steps:
(1) preparation of rigidity aerogel composite: adopt rigid fiber goods as fibre reinforcement, described fibre reinforcement and aerogel precursor liquid solution are undertaken compound by sol-gel, aging, solvent exchange and supercritical drying process, obtain rigidity aerogel composite;
(2) the antiseepage processing of thermal-protective coating: adopt antiseepage primer to soak described rigidity aerogel composite, then in oven dry, so that antiseepage processing is carried out in the surface of described rigidity aerogel composite, thereby obtain thermal-protective coating;
(3) panel reinforcement and thermal-protective coating is compound: adopt fabric as panel reinforcement, described panel reinforcement and described thermal-protective coating are fixed together, then adopt draw point and sew up fibre threads and sew up, obtaining panel reinforcement-thermal-protective coating and make structure;
(4) preparation of ceramic-base panel material: panel reinforcement-thermal-protective coating that step (3) is obtained is made structure and is placed in target profile frock, use ceramic forerunner to flood described panel reinforcement-thermal-protective coating and make structure, then dry, sintering, makes the described high temperature resistant integrative rigidity heat insulating component with ceramic-base panel material.
In some embodiments, carry out described dipping by vacuum hammering method.In some embodiments, the rigid fiber goods in described step (1) are ceramic fiber watt.In some embodiments, described ceramic fiber watt is made by the ceramic fiber of the group of selecting free mullite fiber, aluminum silicate fiber, quartz fibre and alumina fibre to form.In some embodiments, described aerogel precursor liquid solution selects the group of free ethyl orthosilicate, methyl silicate, water glass, Ludox and multi-polysiloxane composition.In some embodiments, the antiseepage primer in described step (2) selects the group of free trim,ethylchlorosilane, silazane, MTMS and hexamethyldisilane composition.In some embodiments, the fabric in described step (3) selects the group of the fabric composition of free quartz fibre, alumina silicate, mullite fiber, alumina fibre, Zirconium oxide fibre.In some embodiments, the material of described stitching fibre threads is identical with the fiber in fabric.In some embodiments, the ceramic forerunner in described step (4) is Ludox and/or aluminium colloidal sol.
For example, described method can be carried out in the following way:
The first step, preparation rigidity aerogel composite,
Adopt rigid fibrous ceramic watt as fibre reinforcement, composite silicon dioxide aerogel precursor liquid solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process; Can adopt common process herein.Ceramic fiber mainly contains mullite fiber, aluminum silicate fiber, quartz fibre, alumina fibre; Aerogel precursor liquid solution can be ethyl orthosilicate, methyl silicate, water glass, Ludox, multi-polysiloxane.
Second step, the antiseepage processing of thermal-protective coating,
Antiseepage processing is carried out in rigidity aerogel composite surface, adopt finite concentration (for example 10-50%, as 10,20,30,40 or 50%) antiseepage primer soak aerogel composite, finally carry out (for example 30 to 90 ℃ of low temperature, for example 60 to 90 ℃, for example 30,40,50,60,70,80 or 90 ℃)) dry, until aerogel composite quality no longer changes; Antiseepage primer can be trim,ethylchlorosilane, silazane, MTMS, hexamethyldisilane.
The 3rd step, panel reinforcement and thermal-protective coating are compound,
Select fabric as panel reinforcement, by profile attaching tooling, panel and thermal-protective coating are clamped, adopt diameter 1mm draw point and sew up fiber and evenly sew up according to needle gage 10-20mm and line-spacing 10-20mm; Fabric is the fabric (for example 2D, 2.5D fabric) of quartz fibre cloth, alumina silicate cloth, mullite fiber cloth, alumina fibre; Sew up fibre threads and select the fiber of the corresponding material of fabric.
The 4th step, prepares ceramic-base panel material,
The material that above-mentioned steps is obtained is placed in target profile frock, adopt vacuum to suppress dipping ceramic forerunner, 80 ℃ of curing 24h, carry out again (for example 30 ℃ to 90 ℃ of cold dryings, for example 30,40,50,60,70,80 or 90 ℃), (for example 800 to 1600 ℃ of high temperature, for example 800,900,1000,1100,1200,1300,1400,1500,1600 ℃) sintering, prepare ceramic-base panel material; Ceramic forerunner is Ludox, aluminium colloidal sol.For example, drying condition can be 30 ℃, humidity 90%1 days, 80%1 days, 70%1 days; High temperature sintering program is that 5h is warming up to 800 ℃, insulation 2h, the rear room temperature that is naturally cooled to.
In the third aspect of the present utility model, provide the high temperature resistant integrative rigidity being made by above-described method heat insulating component.Described in other mode of execution the utility model first aspects or second aspect of the member so making.
Embodiment
Below in conjunction with Fig. 1 and instantiation, the utility model is elaborated.
Adopt 200mm*200mm*20mm rigidity mullite fiber watt as reinforcement, compound teos solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying at 40 ℃, until aerogel composite quality no longer changes, complete the antiseepage processing of thermal-protective coating.Select mullite fiber cloth as panel reinforcement, by frock, panel and thermal-protective coating are clamped, adopt draw point and mullite fiber to sew up according to needle gage 20mm and line-spacing 20mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping aluminium colloidal sol, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Wherein, drying process condition is 30 ℃, humidity 90%1 days, 80%1 days, 70%1 days; High temperature sintering operation is that 5h is warming up to 800 ℃, insulation 2h, the rear room temperature that is naturally cooled to.
Adopt 200mm*200mm*20mm rigidity quartz fibre watt as reinforcement, compound teos solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying, until aerogel composite quality no longer changes, complete the antiseepage processing of thermal-protective coating.Select quartz fibre cloth as panel reinforcement, by frock, panel and thermal-protective coating are clamped, adopt draw point and quartz fibre to sew up according to needle gage 20mm and line-spacing 20mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping Ludox, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Antiseepage oven dry and drying process and high temperature sintering operation are the same.
Adopt 200mm*200mm*20mm rigidity quartz fibre watt as reinforcement, compound methyl silicate solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying, until aerogel composite quality no longer changes, complete the antiseepage processing of thermal-protective coating.Select quartz fibre cloth as panel reinforcement, by frock, panel and thermal-protective coating are clamped, adopt draw point and quartz fibre to sew up according to needle gage 10mm and line-spacing 10mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping Ludox, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Antiseepage oven dry and drying process and high temperature sintering operation are the same.
Embodiment 4
Adopt 200mm*200mm*20mm rigidity alumina fibre watt as reinforcement, comprehensive silicon sol solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying, until aerogel composite quality no longer changes, complete the antiseepage processing of thermal-protective coating.Selective oxidation aluminum fiber cloth, as panel reinforcement, clamps panel and thermal-protective coating by frock, adopts draw point and alumina fibre to sew up according to needle gage 10mm and line-spacing 10mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping aluminium colloidal sol, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Antiseepage oven dry and drying process and high temperature sintering operation are the same.
Embodiment 5
Adopt 200mm*200mm*20mm rigidity aluminum silicate fiber watt as reinforcement, compound methyl silicate solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying, until aerogel composite quality no longer changes, complete the antiseepage processing of thermal-protective coating.Select aluminum silicate fiber cloth as panel reinforcement, by frock, panel and thermal-protective coating are clamped, adopt draw point and aluminum silicate fiber to sew up according to needle gage 10mm and line-spacing 10mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping Ludox, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Antiseepage oven dry and drying process and high temperature sintering operation are the same.
Embodiment 6
Adopt 200mm*200mm*20mm rigidity aluminum silicate fiber watt as reinforcement, compound teos solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying, until aerogel composite quality no longer changes, complete the antiseepage processing of thermal-protective coating.Select aluminum silicate fiber cloth as panel reinforcement, by frock, panel and thermal-protective coating are clamped, adopt draw point and aluminum silicate fiber to sew up according to needle gage 10mm and line-spacing 10mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping Ludox, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Antiseepage oven dry and drying process and high temperature sintering operation are the same.
Embodiment 7
Adopt 200mm*200mm*20mm rigidity aluminum silicate fiber watt as reinforcement, compound teos solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the silicone trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying, until aerogel composite quality no longer changes.Select aluminum silicate fiber cloth as panel reinforcement, by frock, panel and thermal-protective coating are clamped, adopt draw point and aluminum silicate fiber to sew up according to needle gage 10mm and line-spacing 10mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping Ludox, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Antiseepage oven dry and drying process and high temperature sintering operation are the same.
Embodiment 8
Adopt 200mm*200mm*20mm rigidity aluminum silicate fiber watt as reinforcement, compound teos solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying, until aerogel composite quality no longer changes, complete the antiseepage processing of thermal-protective coating.Select aluminum silicate fiber cloth as panel reinforcement, by frock, panel and thermal-protective coating are clamped, adopt draw point and aluminum silicate fiber to sew up according to needle gage 25mm and line-spacing 25mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping Ludox, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Antiseepage oven dry and drying process and high temperature sintering operation are the same.
Embodiment 9
Adopt 200mm*200mm*20mm rigidity Zirconium oxide fibre watt as reinforcement, compound teos solution, the rigidity aerogel composite obtaining by sol-gel process, aging, solvent exchange and supercritical drying process.Adopt the trim,ethylchlorosilane of mass fraction 10% to soak rigidity aerogel composite, after 24h, carry out low temperature drying, until aerogel composite quality no longer changes, complete the antiseepage processing of thermal-protective coating.Select aluminum silicate fiber cloth as panel reinforcement, by frock, panel and thermal-protective coating are clamped, adopt draw point and aluminum silicate fiber to sew up according to needle gage 10mm and line-spacing 10mm.The material that stitching is obtained is placed in profile frock, adopts vacuum to suppress dipping Ludox, and by dry, high temperature sintering operation, prepares ceramic-base panel material, then carry out the further finishing of integral material, obtains high temperature resistant integrative rigidity heat insulating component.Antiseepage oven dry and drying process and high temperature sintering operation are the same.
Table 1 embodiment Data Comparison
Note: heat-shielding performance refers to 800 ℃ of hot sides, 1000s material back of the body temperature, and material back of the body temperature is lower, and heat-shielding performance is better; In embodiment, material therefor is as the criterion so that in table, data are listed.
Claims (7)
1. a high temperature resistant integrative rigidity heat insulating component, is characterized in that, described high temperature resistant integrative rigidity heat insulating component comprises:
Rigid fiber thermal-protective coating;
Infiltrate into the aerogel permeable formation in described rigid fiber thermal-protective coating;
Fabric panel enhancement layer at least one side of described rigid fiber thermal-protective coating.
2. high temperature resistant integrative rigidity heat insulating component as claimed in claim 1, is characterized in that, described high temperature resistant integrative rigidity heat insulating component comprises:
Fabric panel enhancement layer on the both sides of described rigid fiber thermal-protective coating.
3. high temperature resistant integrative rigidity heat insulating component as claimed in claim 1 or 2, is characterized in that, has the outside of the described rigid fiber thermal-protective coating of aerogel permeable formation also to comprise impervious barrier in infiltration.
4. high temperature resistant integrative rigidity heat insulating component as claimed in claim 1 or 2, is characterized in that, the stitching fibre threads identical with fabric panel enhancement layer by material is sewed together described rigid fiber thermal-protective coating and described fabric panel enhancement layer.
5. high temperature resistant integrative rigidity heat insulating component as claimed in claim 4, is characterized in that, the needle gage of making is 10mm to 20mm, and the line-spacing of sewing line is 10mm to 20mm.
6. high temperature resistant integrative rigidity heat insulating component as claimed in claim 4, is characterized in that, described high temperature resistant integrative rigidity heat insulating component also permeates and has ceramic forerunner permeable formation.
7. high temperature resistant integrative rigidity heat insulating component as claimed in claim 5, is characterized in that, described high temperature resistant integrative rigidity heat insulating component also permeates and has ceramic forerunner permeable formation.
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| CN103411098A (en) * | 2013-08-28 | 2013-11-27 | 航天特种材料及工艺技术研究所 | Integrated high-temperature-resistant rigid heat insulation component and production method thereof |
| CN107244881A (en) * | 2014-10-31 | 2017-10-13 | 航天特种材料及工艺技术研究所 | A kind of method for preparing resistance to compression heat-barrier material and resistance to compression heat-barrier material obtained by this method |
| CN108483452A (en) * | 2018-05-29 | 2018-09-04 | 南京工业大学 | Preparation method of low-cost blocky gradient composite aerogel |
| CN109177365A (en) * | 2015-03-30 | 2019-01-11 | 松下知识产权经营株式会社 | A kind of heat Insulation film, using its electronic equipment and heat Insulation film manufacturing method |
| CN110128158A (en) * | 2019-04-22 | 2019-08-16 | 湖南远辉复合材料有限公司 | Solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure and preparation method thereof |
| CN115159954A (en) * | 2022-07-15 | 2022-10-11 | 航天特种材料及工艺技术研究所 | Aerogel thermal insulation layer and preparation method thereof |
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2013
- 2013-08-28 CN CN201320526457.7U patent/CN203628151U/en not_active Expired - Lifetime
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| CN110128158A (en) * | 2019-04-22 | 2019-08-16 | 湖南远辉复合材料有限公司 | Solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure and preparation method thereof |
| CN110128158B (en) * | 2019-04-22 | 2021-11-02 | 湖南远辉复合材料有限公司 | Heat-proof/heat-insulation/load-bearing integrated ceramic-based light sandwich structure and preparation method thereof |
| CN115159954A (en) * | 2022-07-15 | 2022-10-11 | 航天特种材料及工艺技术研究所 | Aerogel thermal insulation layer and preparation method thereof |
| CN115159954B (en) * | 2022-07-15 | 2023-05-09 | 航天特种材料及工艺技术研究所 | Aerogel heat insulation layer and preparation method thereof |
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