1. The high-temperature-resistant heat-proof and heat-insulating material integrated structure based on precursor conversion ceramic is characterized by comprising an outer layer for heat prevention and bearing, an intermediate layer for heat insulation and an inner layer serving as a heat sink structure.

2. The integrated structure of claim 1, further comprising an adhesive layer between the outer layer and the intermediate layer, and between the intermediate layer and the inner layer.

3. The integrated structure of the heat prevention and insulation material as claimed in claim 2, wherein the bonding layer is made of PDCs bonding agent; preferably, the PDCs adhesive is obtained by mixing polycarbosilane, SiC whiskers and Al powder according to the mass ratio of 1:2: 0.2.

4. The integrated structure of claim 1, further comprising a plurality of connectors connecting the outer layer, the middle layer and the inner layer;

preferably, the material of the connecting piece is the same as that of the outer layer;

more preferably, the connecting piece is made of a C/SiC ceramic matrix composite material;

preferably, the connecting piece is a rivet;

preferably, the distance between the connecting pieces is 8-15 mm.

5. The integrated structure of claim 1, wherein the outer layer is made of a ceramic matrix composite material, preferably a C/SiC ceramic matrix composite material.

6. The integrated structure of claim 1, wherein the intermediate layer is made of SiO₂An aerogel.

7. The integrated structure of claim 1, wherein the inner layer is a flat plate made of aluminum.

8. The method for manufacturing the integrated structure of heat prevention and insulation material according to any one of claims 1 to 7, comprising the steps of:

coating an adhesive layer on the outer layer or the 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 a tie layer formed on the intermediate layer structure;

applying a plurality of connectors connecting the outer layer, the intermediate layer and the inner layer on the formed structure;

and carrying out high-temperature treatment on the formed structure to obtain the heat-proof and heat-insulating material integrated structure.

9. The method of claim 8, wherein the high temperature treatment is performed at 200 ℃ for 3 hours.

10. Use of an integrated structure of heat protection and insulation according to any one of claims 1 to 7 for the production of high performance aircraft.

Background

The hypersonic flight vehicle has the characteristics of high flying speed, strong penetration capability and the like, and has become a high-tech field for key development of various military and strong countries. When the aircraft flies in the atmosphere at high speed, the pneumatic heating is very severe and reaches several MW/m²Heat flux density and surface temperature of 2000 ℃ and above for outside of aircraftThermal protection systems for surfaces present a significant challenge. Thermal protection systems need not only withstand extremely high temperature environments, but also have good thermal and mechanical properties to protect equipment internal equipment. The heat protection and insulation functions of the heat protection system are usually completed by different materials, which involves the connection and integration problem among different materials, and the problem is always a key problem that needs to be mainly solved in the design of the hypersonic speed aircraft.

Chinese patent (publication No. CN 109968757A) discloses an ablation-resistant light heat-proof heat-insulation integrated composite material and a preparation method thereof. The composite material is of a sandwich structure, a middle layer takes chopped fibers as a reinforcement, phenolic resin as a matrix, hollow microspheres as a heat insulation filler, upper and lower surface layers are laminated by fiber cloth prepreg, and three layers are co-cured to prepare the composite material. The load-bearing capacity of the material is poor due to the lack of continuous fiber load-bearing inside the material. In addition, the temperature difference between the surface and the inside of the material is extremely large, and the material is easy to crack in the service process and lose the heat-proof function.

Chinese patent (publication No. CN 108517102A) discloses a light heat-proof composite material and a preparation method thereof. Aiming at the short fiber/phenolic resin matrix composite material, the invention introduces light organic fiber and light filling particles for light modification, and the prepared phenolic resin matrix light heat-proof composite material is suitable for mould pressing, isostatic pressing or layering forming of heat-proof products. The bearing performance of the material is poor, the heat resistance and the heat insulation function of the material are realized by the carbonized phenolic resin, the thermal conductivity coefficient is high, and the high-efficiency heat insulation function cannot be met. In addition, the phenolic aldehyde is easy to carbonize and delaminate at high temperature, and can be continuously oxidized and consumed, so that the maintenance of the aerodynamic shape of the aircraft is not facilitated.

In summary, the main disadvantages of the existing heat-proof materials are as follows:

(1) the existing heat-proof material has poor bearing performance and cannot meet the performance requirements of high-speed, large-power and high-performance aircrafts;

(2) most of the existing heat-proof materials rely on the carbonization of phenolic resin at high temperature to realize temperature resistance and heat insulation, the heat conductivity coefficient of the materials is higher, and the pneumatic efficiency of the aircraft is influenced;

(3) the existing heat-proof material has complex preparation process and is difficult to be applied in engineering.

Therefore, the performance of the existing heat-proof and heat-insulating material cannot 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 defects of the prior art, the first object of the invention is to provide an integrated structure of heat and heat prevention and insulation materials based on precursor conversion ceramics (PDCs). The structure can endure extreme high temperature environment, has good heat insulation performance and mechanical property, and can be well used in high-performance aircrafts.

The second purpose of the invention is to provide a method for manufacturing a high-temperature-resistant heat-insulating material integrated structure based on precursor conversion ceramic.

The third purpose of the invention is to provide the application of the high-temperature-resistant heat-insulating material-preventing integrated structure based on the precursor conversion ceramic.

In order to achieve the first purpose, the invention adopts the following technical scheme:

a high-temperature-resistant heat-proof and heat-insulating material integrated structure based on precursor conversion ceramic comprises an outer layer for heat prevention and bearing, an intermediate 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 internal environment. The outer layer has the effects of bearing force and resisting high temperature; the middle layer has the heat insulation effect; the inner layer has the effect of a heat sink.

Further, the integrated structure further comprises a bonding layer, the bonding layer is located between the outer layer and the middle layer, and the bonding layer is located between the middle 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 tie layer functions to bond the outer layer to the intermediate layer, the intermediate layer and the inner layer.

Furthermore, the bonding layer is made of PDCs bonding agent; preferably, the PDCs adhesive is obtained by mixing polycarbosilane, SiC whiskers and Al powder according to the mass ratio of 1:2: 0.2. The technical personnel of the invention find in research that the PDCs adhesive formed by adopting the specific composition has better bonding effect, so that the stability of the obtained structure and the performances of heat insulation, heat resistance, load bearing and the like can meet the severe environment of high-performance aircraft application.

Furthermore, the integrated structure also 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 maximum extent.

Furthermore, 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 no specific requirements are made on the number of the connecting pieces. For example, the distance between the connecting pieces is 8-15 mm. The structural blank formed by the outer layer, the middle layer and the inner layer is punched, and the holes penetrate through the outer layer, the middle layer and the inner layer and are fixed by connecting pieces and rivets. The diameter of the holes can be 2-4mm, the hole spacing is 8-15mm, andthe C/SiC ceramic matrix composite rivet 4 rivets the materials of all 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 SiO₂An aerogel.

Further, the inner layer is an aluminum flat plate.

In order to achieve the second purpose, the invention adopts the following technical scheme:

a method for manufacturing a high-temperature-resistant heat-insulating material integrated structure based on precursor conversion ceramic comprises the following steps:

coating an adhesive layer on the outer layer or the 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 a tie layer formed on the intermediate layer structure;

applying a plurality of connectors connecting the outer layer, the intermediate layer and the inner layer on the formed structure;

and carrying out high-temperature treatment on the formed structure to obtain the heat-proof and heat-insulating material integrated structure.

Wherein, as will be appreciated by those skilled in the art, in the above-described fabrication method, when applying the adhesive layer to the outer layer, the inner layer is correspondingly applied subsequently on the adhesive layer formed on the intermediate layer structure; when applying a tie layer on the inner layer, the outer layer is correspondingly subsequently applied on the tie layer formed on the intermediate layer structure.

Further, in the manufacturing method, the outer layer, the middle layer and the inner layer are cleaned before use, then surface dust or other attachments are removed, and then the outer layer, the middle layer and the inner layer are dried for use.

Further, the manner of application is 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-proof performance, heat-insulating performance, mechanical performance and the like of the obtained integrated structure are more stable.

In order to achieve the third purpose, the invention adopts the following technical scheme:

the application of the integrated structure of the heat-proof and heat-insulating material in the preparation of a high-performance aircraft. The integrated structure can be used as a high-performance aircraft heat-proof and heat-insulating material.

The high performance aircraft includes, but is not limited to, a hypersonic aircraft.

The invention has the following beneficial effects:

the heat-proof and heat-insulating material integrated structure provided by the invention has the performances of bearing force, heat prevention, heat insulation, heat sink and the like, has excellent heat-insulating 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 heat-insulating material integrated structure prepared by the invention has stable structure and outstanding shock resistance. The noise test can meet 160dB noise test and passes the vibration test examination under the acceleration of 100G.

Drawings

The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.

FIG. 1 is a schematic structural diagram of an integrated structure of a high temperature resistant and heat insulating material based on precursor conversion ceramics in the present invention.

Detailed Description

In order to more clearly illustrate the invention, the invention is further described below with reference to preferred embodiments and the accompanying drawings. Similar parts in the figures 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 is not to be taken as limiting the scope of the invention.

One embodiment of the invention provides an integrated structure of heat prevention and insulation materials based on precursor conversion ceramics (PDCs), which has a schematic structural diagram shown in figure 1 and comprises an outer layer 1 for heat prevention and bearing, an intermediate layer 2 for heat insulation, an inner layer 3 serving as a heat sink structure, and 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 in addition, the integrated structure also comprises a connecting piece 4 for 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 material, preferably a C/SiC ceramic matrix composite material.

Illustratively, the material of the intermediate layer 2 is SiO₂An aerogel.

Illustratively, the inner layer 3 is a flat plate of aluminum.

Illustratively, the material of the bonding layer 5 is PDCs bonding agent; preferably, the PDCs adhesive is obtained by mixing polycarbosilane, SiC whiskers and Al powder according to the mass ratio of 1:2: 0.2.

Illustratively, the material of the connecting piece 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 maximum extent.

Illustratively, the connecting piece 4 is made of a C/SiC ceramic matrix composite material.

Illustratively, the connecting member 4 is a rivet.

Furthermore, the arrangement of the connecting pieces 4 in the structure can be uniformly distributed, and no specific requirement is made on the number of the connecting pieces 4. For example, the distance between the connecting elements 4 is 8-15 mm. The structural blank formed by the outer layer 1, the middle layer 2 and the inner layer 3 is punched, 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 hole spacing is 8-15mm, andthe C/SiC ceramic matrix composite rivet rivets the materials of all layers together.

Another embodiment of the present invention provides a method for manufacturing an integrated heat-proof and heat-insulating material structure based on precursor conversion ceramics (PDCs), comprising:

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 a tie layer 5 formed on the structure of the intermediate layer 2;

applying a plurality of connecting elements 4 connecting the outer layer 1, the intermediate layer 2 and the inner layer 3 on the formed structure;

and 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 outer layer, the middle layer and the inner layer are dried for use.

Further, the manner of application is pressing.

Further, the temperature of the high-temperature treatment is 200 ℃ and the time is 3 hours.

The technical solution of the present invention is described below with reference to some specific examples:

example 1

Mixing 3mm thick C/SiC flat plate and 5mm thick SiO₂Cleaning aerogel and a flat plate made of aluminum with the thickness of 2mm, and drying;

uniformly mixing polycarbosilane, SiC crystal whisker and Al powder in a weight ratio of 1:2:0.2 to prepare a PDCs adhesive;

mixing a C/SiC flat plate with SiO₂Between aerogels, and SiO₂Brushing the prepared PDCs adhesive between the aerogel and the aluminum flat plate, pressing and fixing to form an anti-heat insulation blank material;

punching holes with the diameter of 3.5mm and the hole interval of 10mm on the heat-insulating blank material with the diameter of 3.50 mm₀ ^+0.05The C/SiC rivets rivet the materials of all layers together;

and (3) placing the riveted heat-proof blank material in an oven, and treating at the high temperature of 200 ℃ for 3 hours to finish the preparation of the heat-proof and heat-insulating material integrated structure.

The surface temperature rise of the C/SiC composite material with the heat-insulating material integrated structure obtained in the embodiment is less than 70 ℃ under the condition of 1 minute 1100 ℃ temperature rise of the surface of the aluminum plate. The test method meets the 160dB noise test and passes the vibration test examination under the acceleration of 100G.

Example 2

Mixing 5mm thick C/SiC flat plate and 10mm thick SiO₂Cleaning aerogel and a flat plate made of aluminum with the thickness of 2mm, and drying;

uniformly mixing polycarbosilane, SiC crystal whisker and Al powder in a weight ratio of 1:2:0.2 to prepare a PDCs adhesive;

mixing a C/SiC flat plate with SiO₂Between aerogels, and SiO₂Brushing the prepared PDCs adhesive between the aerogel and the aluminum flat plate, pressing and fixing to form an anti-heat insulation blank material;

punching holes with the diameter of 3mm and the hole interval of 12 mm on the heat-insulating blank material with the diameter of 3.0₀ ^+0.05The C/SiC rivets rivet the materials of all layers together;

and (3) placing the riveted heat-proof blank material in an oven, and treating at the high temperature of 200 ℃ for 3 hours to finish the preparation of the heat-proof and heat-insulating material integrated structure.

The surface temperature rise of the C/SiC composite material with the heat-insulating material integrated structure obtained in the embodiment is less than 60 ℃ under the condition that the surface temperature rise is 1100 ℃ for 1 minute. The test method meets the 160dB noise test and passes the vibration test examination under the acceleration of 100G.

Example 3

Mixing 5mm thick C/SiC flat plate and 10mm thick SiO₂Cleaning aerogel and a flat plate made of aluminum with the thickness of 5mm, and drying;

uniformly mixing polycarbosilane, SiC crystal whisker and Al powder in a weight ratio of 1:2:0.2 to prepare a PDCs adhesive; mixing a C/SiC flat plate with SiO₂Between aerogels, and SiO₂Brushing the prepared PDCs adhesive between the aerogel and the aluminum flat plate, pressing and fixing to form an anti-heat insulation blank material;

punching holes with the diameter of 2.5 mm and the hole interval of 15mm on the heat-insulating blank material with the diameter of 2.50 mm₀ ^+0.05The C/SiC rivets rivet the materials of all layers together;

and (3) placing the riveted heat-proof blank material in an oven, and treating at the high temperature of 200 ℃ for 3 hours to finish the preparation of the heat-proof and heat-insulating material integrated structure.

The surface temperature rise of the C/SiC composite material with the heat-insulating material integrated structure obtained in the embodiment is less than 55 ℃ under the condition of 1 minute 1100 ℃. The test method meets the 160dB noise test and passes the vibration test examination under the acceleration of 100G.

Comparative example 1

Example 1 is repeated, except that the PDCs binder is replaced with polycarbosilane, SiC whiskers and Al powder mixed in a mass ratio of 1:2.5:0.2, and the remaining conditions are unchanged, to prepare an integrated structure of the thermal insulation prevention and insulation material.

The properties of the structure are: the temperature rise of the surface of the aluminum plate is less than 70 ℃ under the condition that the temperature rise of the surface of the C/SiC composite material is 1100 ℃ for 1 minute. The test method meets the 160dB noise test, cannot pass the vibration test examination under the acceleration of 100G, and the structure generates obvious cracks under the condition.

It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.