CN113400734B - High-temperature-resistant heat-proof and heat-insulating material integrated structure based on precursor conversion ceramic, and manufacturing method and application thereof - Google Patents
High-temperature-resistant heat-proof and heat-insulating material integrated structure based on precursor conversion ceramic, and manufacturing method and application thereof Download PDFInfo
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Classifications
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- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
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- B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
- B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
- B32B3/085—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts spaced apart pieces on the surface of a layer
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- B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
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Abstract
The invention discloses a high-temperature-resistant heat-proof material integrated structure based on precursor conversion ceramics, which comprises an outer layer for heat prevention and bearing, a middle layer for heat insulation and an inner layer serving as a heat sink structure. The structure can withstand extremely high temperature environment, has good heat insulation performance and mechanical property, and can be well used in high-performance aircrafts. The invention also discloses a manufacturing method and application of the integrated structure.
Description
Technical Field
The present invention relates to high performance aircraft thermal protection. More particularly, relates to a high-temperature-resistant heat-proof and insulating material integrated structure based on precursor conversion ceramics, and a manufacturing method and application thereof.
Background
Hypersonic aircrafts have the characteristics of high flying speed, strong outburst prevention capability and the like, and have become the high technical field of important development of military countries. When an aircraft is flown at high speeds in the atmosphere, pneumatic heating is very severe, heat flux densities up to several MW/m 2 and surface temperatures of 2000 ℃ and above pose serious challenges to the thermal protection system of the aircraft exterior surface. The thermal protection system is required to not only withstand extremely high temperature environments, but also have good heat insulating properties and mechanical properties to protect the equipment internal equipment. The heat protection and insulation functions of the thermal protection system usually require different materials for their completion, which involves the problem of connection and integration between the different materials, and this problem has been a critical problem that the hypersonic aircraft design needs to solve with great importance.
Chinese patent (publication No. CN 109968757A) discloses an ablation-resistant light heat-proof heat-insulating integrated composite material and a preparation method thereof. The ablation-resistant light heat-proof integrated composite material is of a sandwich structure, wherein a middle layer takes chopped fibers as a reinforcing body, phenolic resin as a matrix and hollow microspheres as heat-proof filler, an upper surface layer and a lower surface layer are bonded by adopting fiber cloth prepreg, and three layers are co-cured to prepare the composite material. The material is less than good in its load carrying capacity due to the lack of continuous fiber load carrying within the material. In addition, the temperature difference between the surface and the inside of the material is extremely large, so that cracking is easy to cause in the service process, and the heat-proof and heat-insulating functions are lost.
Chinese patent (publication No. CN 108517102A) discloses a light heat-proof and heat-insulating composite material and a preparation method thereof. The invention introduces light organic fiber and light filling particles for light modification aiming at the short fiber/phenolic resin matrix composite material, and the prepared phenolic resin matrix light heat-proof and heat-proof composite material is suitable for compression molding, isostatic pressing or layering molding of heat-proof products. The material has poor bearing performance, and the heat resistance and heat insulation functions of the material are realized by carbonized phenolic resin, so that the material has high thermal conductivity and cannot meet the high-efficiency heat insulation function. In addition, phenolic aldehyde is easy to carbonize and delaminate at high temperature, and meanwhile, the phenolic aldehyde is continuously oxidized and consumed, so that the pneumatic appearance of the aircraft is not easy to maintain.
In summary, the main disadvantages of the conventional heat insulation materials are as follows:
(1) The existing heat-proof and insulating material has poor bearing performance and can not meet the performance requirements of high-speed and large-maneuvering high-performance aircrafts;
(2) Most of the existing heat-proof and heat-proof materials are carbonized by phenolic resin at high temperature to realize temperature resistance and heat insulation, and the heat conductivity coefficient of the materials is higher, and the aerodynamic efficiency of an aircraft is influenced;
(3) The existing heat-proof and insulating material has complex preparation process and is difficult to engineer and apply.
Therefore, the performance of the existing heat-proof and insulating material can not meet the comprehensive performance requirements of high bearing capacity, high heat resistance and low heat conductivity of a high-performance aircraft.
Disclosure of Invention
Based on the shortcomings of the prior art, a first object of the present invention is to provide an integrated structure of heat insulating materials based on precursor-transformed ceramics (PDCs). The structure can withstand extremely high temperature environment, has good heat insulation performance and mechanical property, and can be well used in high-performance aircrafts.
The second aim of the invention is to provide a manufacturing method of the high-temperature-resistant heat-proof material integrated structure based on precursor conversion ceramics.
The third object of the invention is to provide an application of a high-temperature-resistant heat-proof material integrated structure based on precursor conversion ceramics.
In order to achieve the first object, the present invention adopts the following technical scheme:
A high-temperature-resistant heat-proof material integrated structure based on precursor conversion ceramics comprises an outer layer for heat prevention and bearing, a middle layer for heat insulation and an inner layer serving as a heat sink structure.
It is understood that the outer layer in the structure refers to the layer of the structure that is in contact with the outside world and the inner layer refers to the layer of the structure that is in contact with the inside environment. The outer layer has the effects of bearing force and high temperature resistance; the middle layer has the heat insulation effect; the inner layer has the effect of a heat sink.
Further, the integrated structure further includes an adhesive layer located between the outer layer and the intermediate layer, and the adhesive layer is located between the intermediate layer and the inner layer. That is, adhesive layers are provided between the outer layer and the intermediate layer, and between the intermediate layer and the inner layer. The adhesive layer functions to bond the outer layer with the intermediate layer, the intermediate layer and the inner layer.
Further, the bonding layer is made of PDCs bonding agent; preferably, the PDCs binder is obtained by mixing polycarbosilane, siC whisker and Al powder according to a mass ratio of 1:2:0.2. The technical staff of the invention find that the bonding effect of the PDCs bonding agent formed by adopting the specific composition is better, so that the stability of the obtained structure, heat insulation, heat resistance, bearing and other performances can meet the severe environment of high-performance aircraft application.
Further, the integrated structure further comprises a plurality of connecting pieces for connecting the outer layer, the middle layer and the inner layer.
Further, the material of the connecting piece is the same as that of the outer layer. The connecting piece and the outer layer are made of the same material, so that the stability of the structure can be guaranteed to the greatest extent.
Further, the connecting piece is made of a C/SiC ceramic matrix composite material.
Further, the connecting piece is a rivet.
Furthermore, the arrangement of the connecting pieces in the structure can be uniformly distributed, and the number of the connecting pieces is not particularly required. For example, the distance between the connectors is 8-15mm. The structural blank formed by the outer layer, the middle layer and the inner layer is perforated, and the holes penetrate through the outer layer, the middle layer and the inner layer and are fixed by connecting piece rivets. The diameter of the holes can be 2-4mm, the distance between the holes is 8-15mm, and the method adoptsThe C/SiC ceramic matrix composite rivet 4 rivets the layers together.
Further, the outer layer is made of a ceramic matrix composite material.
Further, the outer layer is made of a C/SiC ceramic matrix composite material.
Further, the intermediate layer is made of SiO 2 aerogel.
Further, the inner layer is an aluminum flat plate.
In order to achieve the second object, the present invention adopts the following technical scheme:
A manufacturing method of a high-temperature-resistant heat-proof material integrated structure based on precursor conversion ceramics comprises the following steps:
coating an adhesive layer on the outer or inner layer structure;
Applying an intermediate layer structure on the tie layer;
coating an adhesive layer on the intermediate layer structure;
Applying the inner or outer layer over an adhesive layer formed on the intermediate layer structure;
Applying a plurality of connectors to the formed structure to connect the outer layer, intermediate layer and inner layer;
and (3) carrying out high-temperature treatment on the formed structure to obtain the heat-proof and heat-insulating material integrated structure.
Wherein, in the above-described fabrication method, when the adhesive layer is applied to the outer layer, the inner layer is applied to the adhesive layer formed on the intermediate layer structure at a corresponding subsequent time, as will be appreciated by those skilled in the art; when the inner layer is coated with an adhesive layer, the outer layer is applied to the adhesive layer formed on the intermediate layer structure at a corresponding subsequent time.
In the manufacturing method, the outer layer, the middle layer and the inner layer are cleaned before use, surface dust or other attachments are removed, and then the outer layer, the middle layer and the inner layer are dried and reused.
Further, the applying is by pressing.
Further, the temperature of the high temperature treatment is 200 ℃ and the time is 3 hours. The high-temperature treatment condition ensures that the structure, heat resistance, heat insulation performance, mechanical performance and the like of the obtained integrated structure are more stable.
In order to achieve the third object, the present invention adopts the following technical scheme:
The application of the integrated structure of the heat-proof and insulating material in preparing high-performance aircrafts. The integrated structure can be used as a high-performance aircraft heat-proof and insulating material.
Wherein the high performance aircraft includes, but is not limited to, hypersonic aircraft.
The beneficial effects of the invention are as follows:
The heat-proof and insulating material integrated structure provided by the invention has the performances of bearing, heat prevention, heat insulation, heat sink and the like, has excellent heat insulation performance, and can meet the requirement that the surface temperature rise of an aluminum plate is less than 100 ℃ under the condition that the surface temperature rise of a C/SiC composite material is 1100 ℃ for 1 minute.
The heat-proof and insulating material integrated structure prepared by the invention has stable structure and outstanding impact resistance. 160dB noise test can be satisfied, and the test is checked through a vibration test under 100G acceleration.
Drawings
The following describes the embodiments of the present invention in further detail with reference to the drawings.
Fig. 1 shows a schematic structural diagram of an integrated structure of a high-temperature-resistant heat-proof material based on precursor-transformed ceramics in the present invention.
Detailed Description
In order to more clearly illustrate the present invention, the present invention will be further described with reference to preferred embodiments and the accompanying drawings. Like parts in the drawings are denoted by the same reference numerals. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and that this invention is not limited to the details given herein.
An embodiment of the present invention provides an integrated structure of heat-proof materials based on precursor transformed ceramics (PDCs), the structure of which is schematically shown in fig. 1, and the integrated structure comprises an outer layer 1 for heat protection and bearing, an intermediate layer 2 for heat insulation, an inner layer 3 as a heat sink structure, bonding layers 5 respectively positioned between the outer layer 1 and the intermediate layer 2 and between the intermediate layer 2 and the inner layer 3, and a connecting piece 4 connecting the outer layer 1, the intermediate layer 2, the inner layer 3 and the bonding layers 5.
Illustratively, the material of the outer layer 1 is a ceramic matrix composite, preferably a C/SiC ceramic matrix composite.
Illustratively, the material of the intermediate layer 2 is SiO 2 aerogel.
The inner layer 3 is illustratively a flat plate of aluminum.
Illustratively, the material of the adhesive layer 5 is PDCs adhesive; preferably, the PDCs binder is obtained by mixing polycarbosilane, siC whisker and Al powder according to a mass ratio of 1:2:0.2.
Illustratively, the material of the connecting member 4 is the same as that of the outer layer 1. The connecting piece and the outer layer are made of the same material, so that the stability of the structure can be guaranteed to the greatest extent.
Illustratively, the material of the connecting piece 4 is a C/SiC ceramic matrix composite.
Illustratively, the connector 4 is a rivet.
Furthermore, the arrangement of the connecting pieces 4 in the structure can be uniformly distributed, and the number of the connecting pieces 4 is not particularly required. For example, the distance between the connectors 4 is 8-15mm. The structural blank formed by the outer layer 1, the middle layer 2 and the inner layer 3 is perforated, and the holes penetrate through the outer layer 1, the middle layer 2 and the inner layer 3 and are fixed by rivets through the connecting pieces 4. The diameter of the holes can be 2-4mm, the distance between the holes is 8-15mm, and the method adoptsThe C/SiC ceramic matrix composite rivet rivets the layers together.
Still another embodiment of the present invention provides a method for manufacturing an integrated structure of heat shielding materials based on precursor-transformed ceramics (PDCs):
coating an adhesive layer 5 on the outer layer 1 or the inner layer 3 structure;
applying an intermediate layer 2 structure on said bond 5;
Coating an adhesive layer 5 on the intermediate layer 2 structure;
applying the inner layer 3 or the outer layer 1 on an adhesive layer 5 formed on the structure of the intermediate layer 2;
applying a number of connectors 4 connecting the outer layer 1, the intermediate layer 2 and the inner layer 3 on the formed structure;
and (3) carrying out high-temperature treatment on the formed structure to obtain the heat-proof and heat-insulating material integrated structure.
In the manufacturing method, the outer layer 1, the middle layer 2 and the inner layer 3 are cleaned before use, surface dust or other attachments are removed, and then the materials are dried and used.
Further, the applying is by pressing.
Further, the temperature of the high temperature treatment is 200 ℃ and the time is 3 hours.
The following describes the technical scheme of the present invention with reference to some specific embodiments:
Example 1
Cleaning and drying a C/SiC flat plate with the thickness of 3mm, siO 2 aerogel with the thickness of 5mm and an aluminum flat plate with the thickness of 2 mm;
Uniformly mixing polycarbosilane and SiC whisker in a weight ratio of Al powder=1:2:0.2 to prepare a PDCs adhesive;
Brushing the prepared PDCs adhesive between the C/SiC flat plate and the SiO 2 aerogel and between the SiO 2 aerogel and the aluminum flat plate, pressing and fixing to form an anti-heat insulation blank material;
punching the heat-proof blank material, wherein the diameter of the holes is 3.5mm, the distance between the holes is 10mm, and riveting all layers of materials together by adopting C/SiC rivets with phi of 3.50 0 +0.05;
And placing the riveted heat-proof blank material in an oven, and treating at a high temperature of 200 ℃ for 3 hours to complete the preparation of the heat-proof material integrated structure.
The surface temperature rise of the aluminum plate is less than 70 ℃ under the condition that the surface temperature rise of the C/SiC composite material with the heat-proof and insulating material integrated structure is 1 minute and 1100 ℃. The 160dB noise test is satisfied, and the test is checked through a vibration test under 100G acceleration.
Example 2
Cleaning and drying a C/SiC flat plate with the thickness of 5mm, siO 2 aerogel with the thickness of 10mm and an aluminum flat plate with the thickness of 2 mm;
Uniformly mixing polycarbosilane and SiC whisker in a weight ratio of Al powder=1:2:0.2 to prepare a PDCs adhesive;
Brushing the prepared PDCs adhesive between the C/SiC flat plate and the SiO 2 aerogel and between the SiO 2 aerogel and the aluminum flat plate, pressing and fixing to form an anti-heat insulation blank material;
Punching the heat-proof blank material, wherein the hole diameter is 3mm, the hole spacing is 12 mm, and all layers of materials are riveted together by adopting C/SiC rivets with phi of 3.0 and 0 +0.05;
And placing the riveted heat-proof blank material in an oven, and treating at a high temperature of 200 ℃ for 3 hours to complete the preparation of the heat-proof material integrated structure.
The surface temperature rise of the aluminum plate is less than 60 ℃ under the condition that the surface temperature rise of the C/SiC composite material with the heat-proof and insulating material integrated structure is 1 minute and 1100 ℃. The 160dB noise test is satisfied, and the test is checked through a vibration test under the acceleration of 100G.
Example 3
Cleaning and drying a C/SiC flat plate with the thickness of 5mm, siO 2 aerogel with the thickness of 10mm and an aluminum flat plate with the thickness of 5 mm;
Uniformly mixing polycarbosilane and SiC whisker in a weight ratio of Al powder=1:2:0.2 to prepare a PDCs adhesive; brushing the prepared PDCs adhesive between the C/SiC flat plate and the SiO 2 aerogel and between the SiO 2 aerogel and the aluminum flat plate, pressing and fixing to form an anti-heat insulation blank material;
Punching the heat-proof blank material, wherein the diameter of the holes is 2.5 mm, the distance between the holes is 15mm, and riveting all layers of materials together by adopting C/SiC rivets with phi of 2.50 0 +0.05;
And placing the riveted heat-proof blank material in an oven, and treating at a high temperature of 200 ℃ for 3 hours to complete the preparation of the heat-proof material integrated structure.
The surface temperature rise of the aluminum plate is less than 55 ℃ under the condition that the surface temperature rise of the C/SiC composite material with the heat-proof and insulating material integrated structure is 1 minute and 1100 ℃. The 160dB noise test is satisfied, and the test is checked through a vibration test under the acceleration of 100G.
Comparative example 1
Example 1 was repeated except that the PDCs binder was replaced with polycarbosilane, siC whiskers and Al powder in a mass ratio of 1:2.5:0.2, and the rest conditions were unchanged, to prepare an insulating material integrated structure.
The performance of this structure is: the surface temperature rise of the aluminum plate is less than 70 ℃ under the condition of 1100 ℃ for 1 minute on the surface of the C/SiC composite material. The 160dB noise test is satisfied, the test cannot be checked through a vibration test under the acceleration of 100G, and obvious cracks are generated on the structure under the condition.
It should be understood that the foregoing examples of the present invention are provided merely for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention, and that various other changes and modifications may be made therein by one skilled in the art without departing from the spirit and scope of the present invention as defined by the appended claims.
Claims (4)
1. The high-temperature-resistant heat-proof material integrated structure based on precursor conversion ceramics for preparing the high-performance aircraft is characterized by comprising the following parts:
The heat-proof and stress-bearing heat-insulating material comprises an outer layer, an intermediate layer, an inner layer and an adhesive layer, wherein the inner layer is used as a heat sink structure, the adhesive layer is positioned between the outer layer and the intermediate layer, and the adhesive layer is positioned between the intermediate layer and the inner layer; and
A plurality of connecting pieces for connecting the outer layer, the middle layer and the inner layer;
the bonding layer is made of PDCs bonding agent; the PDCs binder is obtained by mixing polycarbosilane, siC whisker and Al powder according to the mass ratio of 1:2:0.2;
The outer layer is made of a C/SiC ceramic matrix composite material;
the intermediate layer is made of SiO 2 aerogel;
the inner layer is an aluminum flat plate;
the material of the connecting piece is the same as that of the outer layer;
the connecting piece is a rivet;
the distance between the connecting pieces is 8-15mm.
2. The method of manufacturing an integrated structure of heat shielding material according to claim 1, comprising the steps of:
coating an adhesive layer on the outer or inner layer structure;
Applying an intermediate layer structure on the tie layer;
coating an adhesive layer on the intermediate layer structure;
Applying the inner or outer layer over an adhesive layer formed on the intermediate layer structure;
Applying a plurality of connectors to the formed structure to connect the outer layer, intermediate layer and inner layer;
and (3) carrying out high-temperature treatment on the formed structure to obtain the heat-proof and heat-insulating material integrated structure.
3. The method according to claim 2, wherein the high temperature treatment is performed at 200 ℃ for 3 hours.
4. Use of the insulation material integrated structure of claim 1 for the manufacture of high performance aircraft.
Priority Applications (1)
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02269038A (en) * | 1988-10-21 | 1990-11-02 | Battelle Memorial Inst | Laminated material |
| CN103723269A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Thermal protection structure |
| CN106584942A (en) * | 2016-12-07 | 2017-04-26 | 航天特种材料及工艺技术研究所 | External thermal insulation material and preparation method thereof |
| CN207748009U (en) * | 2017-12-27 | 2018-08-21 | 中国航天空气动力技术研究院 | A kind of reusable non-ablative thermal protection structure of non-heat short circuit |
| CN109532143A (en) * | 2018-12-04 | 2019-03-29 | 北京机电工程研究所 | Anti-/heat-insulated stealthy integrated covering of one kind and preparation method thereof |
| 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 |
| CN110563955A (en) * | 2019-10-24 | 2019-12-13 | 中国科学院宁波材料技术与工程研究所 | Liquid curable metal-based polycarbosilane and preparation method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US9764987B2 (en) * | 2012-03-02 | 2017-09-19 | Dynamic Material Systems, LLC | Composite ceramics and ceramic particles and method for producing ceramic particles and bulk ceramic particles |
-
2020
- 2020-03-16 CN CN202010181596.5A patent/CN113400734B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02269038A (en) * | 1988-10-21 | 1990-11-02 | Battelle Memorial Inst | Laminated material |
| CN103723269A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Thermal protection structure |
| CN106584942A (en) * | 2016-12-07 | 2017-04-26 | 航天特种材料及工艺技术研究所 | External thermal insulation material and preparation method thereof |
| CN207748009U (en) * | 2017-12-27 | 2018-08-21 | 中国航天空气动力技术研究院 | A kind of reusable non-ablative thermal protection structure of non-heat short circuit |
| CN109532143A (en) * | 2018-12-04 | 2019-03-29 | 北京机电工程研究所 | Anti-/heat-insulated stealthy integrated covering of one kind and preparation method thereof |
| 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 |
| CN110563955A (en) * | 2019-10-24 | 2019-12-13 | 中国科学院宁波材料技术与工程研究所 | Liquid curable metal-based polycarbosilane and preparation method thereof |
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