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CN114163260A - A ceramic matrix composite material system on the surface of unmanned aerial vehicle and preparation method thereof - Google Patents

A ceramic matrix composite material system on the surface of unmanned aerial vehicle and preparation method thereof Download PDF

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CN114163260A
CN114163260A CN202111218198.7A CN202111218198A CN114163260A CN 114163260 A CN114163260 A CN 114163260A CN 202111218198 A CN202111218198 A CN 202111218198A CN 114163260 A CN114163260 A CN 114163260A
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layer
matrix composite
ceramic matrix
spraying
thickness
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CN114163260B (en
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冯晶
陈琳
罗可人
张陆洋
王建坤
刘杰
张义平
江济
胡刚毅
毛福春
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Yunnan Anquan Xiaofang New Material Co ltd
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YUNNAN POLICE OFFICER ACADEMY
Kunming University of Science and Technology
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Publication of CN114163260A publication Critical patent/CN114163260A/en
Priority to JP2024518262A priority patent/JP7728612B2/en
Priority to EP22882640.0A priority patent/EP4421206A4/en
Priority to PCT/CN2022/123842 priority patent/WO2023066030A1/en
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    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
    • C04B41/81—Coating or impregnation
    • C04B41/89—Coating or impregnation for obtaining at least two superposed coatings having different compositions
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
    • C04B41/52—Multiple coating or impregnating multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles

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Abstract

The invention discloses a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof, and the ceramic matrix composite system comprises a ceramic matrix composite substrate, wherein the ceramic matrix composite substrate is covered on the surface of an aircraft body, and a bonding layer, an oxygen barrier layer, an oxygen propagation barrier layer, a thermal expansion coefficient buffer layer and a heat insulation and cooling layer are sequentially deposited on the ceramic matrix composite substrate; wherein the thickness of the bonding layer is 100-200 μm, the thickness of the oxygen propagation resisting layer is 30-50 μm, the thickness of the thermal expansion coefficient buffer layer is 30-50 μm, and the thickness of the heat insulation and temperature reduction layer is 100-1000 μm. The ceramic matrix composite system prepared by the invention has a remarkable high-temperature-resistant, high-heat-insulation, antioxidant and high-oxygen-resistant coating, so that the ceramic matrix composite system can be used for long-term service in high-temperature fire rescue, the service temperature exceeds 1000 ℃, the temperature of internal parts of the unmanned aerial vehicle for fire scene rescue is ensured to be below the limit working temperature, and meanwhile, the surface ceramic matrix composite ceramic material has extremely strong antioxidant performance.

Description

Ceramic matrix composite system on surface of unmanned aerial vehicle and preparation method thereof
Technical Field
The invention relates to the technical field of materials, in particular to a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof.
Background
With the deep research and application of the unmanned aerial vehicle, the maximum takeoff weight of the unmanned aerial vehicle reaches more than ten tons at present, the unmanned low-altitude aircraft is used for carrying out tasks such as fire extinguishing action, personnel rescue, communication connection, substance conveying and the like on a fire rescue site, the danger of a traditional pilot when the traditional pilot carries out the task can be effectively reduced, and meanwhile, the unmanned low-altitude aircraft has the advantages of small size, easiness in operation, small limitation on the takeoff site when carrying out fire rescue in a city, and is more suitable for the modern development trend. However, in order to effectively reduce the weight of the aircraft itself and at the same time increase the substances that it can carry. However, in the prior art, different resin-based composite materials or ceramic-based composite materials are generally used for manufacturing the fuselage of the low-altitude aircraft; the resin-based composite material has the problems of low melting point, insufficient high-temperature resistance and failure caused by smoke corrosion on a fire scene, so that the application of the resin-based composite material in large-scale fire and high-temperature fire scenes is limited; the ceramic matrix composite is silicon carbide fiber reinforced silicon carbide, carbon fiber reinforced carbon, carbon fiber reinforced silicon carbide, silicon carbide fiber reinforced carbon ceramic matrix composite and the like, the melting point of the ceramic matrix composite exceeds 2000 ℃, and the ceramic matrix composite has the advantages of low density, strong plasticity, high specific strength and the like similar to those of resin matrix composites, but the ceramic matrix composite has the defect that contact air at high temperature can be oxidized and failed, and a fire rescue unmanned aerial vehicle needs to be in service in a high-temperature environment for a long time, and simultaneously provides the effects of heat insulation and temperature reduction to ensure that internal parts of the unmanned aerial vehicle are below the limit working temperature. Therefore, the ability of providing oxidation resistance and oxygen transmission resistance for the ceramic matrix composite is the key for realizing the application of the ceramic matrix composite in the fire rescue unmanned aerial vehicle.
In view of the above, there is a need to develop a ceramic matrix composite system for unmanned aerial vehicle surface and a method for preparing the same to solve the above technical problems.
Disclosure of Invention
The invention provides a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof, which are used for solving the problems that the surface material of the body of the fire rescue unmanned aerial vehicle cannot resist high temperature and oxidation and the ceramic matrix composite is difficult to apply at high temperature; according to the invention, the working temperature of the silicon carbide fiber reinforced silicon carbide, the carbon fiber reinforced carbon, the carbon fiber reinforced silicon carbide and the silicon carbide fiber reinforced carbon ceramic matrix composite matrix in the air exceeds 1000 ℃, and the related rescue unmanned aerial vehicle can be in service in a fire rescue field for a long time.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention provides a ceramic matrix composite system on the surface of an unmanned aerial vehicle, which comprises a ceramic matrix composite substrate, wherein the ceramic matrix composite substrate is covered on the surface of an aircraft body, and a bonding layer, an oxygen barrier layer, an oxygen propagation barrier layer, a thermal expansion coefficient buffer layer and a heat insulation and cooling layer are sequentially prepared on the ceramic matrix composite substrate; wherein the thickness of the bonding layer is 100-200 μm, the thickness of the oxygen propagation resisting layer is 30-50 μm, the thickness of the thermal expansion coefficient buffer layer is 30-50 μm, and the thickness of the heat insulation and temperature reduction layer is 100-1000 μm.
Preferably, the thermal expansion coefficient of the oxygen propagation blocking layer is 3 to 6 x 10-6K-1The buffer layer has a thermal expansion coefficient of 6-9 × 10-6K-1The thermal expansion coefficient of the heat insulation and temperature reduction layer is 9-11 multiplied by 10-6K-1。
Preferably, the ceramic matrix composite substrate is one of silicon carbide fiber reinforced silicon carbide, carbon fiber reinforced carbon, carbon fiber reinforced silicon carbide and silicon carbide fiber reinforced carbon.
Preferably, the bonding layer is formed by spraying a Ta material on the surface of the ceramic matrix composite substrate by a cold spraying method.
By adopting the method, the metal tantalum with excellent chemical compatibility with the ceramic matrix composite is selected as the bonding layer, so that the reaction between the matrix material and the bonding layer can be effectively inhibited, and the long-term effective service of the coating is ensured; the compact tantalum coating can be prepared in a cold spraying or electron beam physical vapor deposition mode, the interior of the coating is not oxidized, and the surface of the metal tantalum is in contact with air and oxidized to form a compact oxygen barrier layer Ta after the metal tantalum is placed in the air for a period of time2O5And the process is simplified.
Preferably, the oxygen barrier layer is Ta2O5。
Preferably, the oxygen transmission resisting layer is rare earth tantalate (RETaO)4A ceramic coating; wherein RE is composed of one or more of rare earth elements.
Preferably, the thermal expansion coefficient buffer layer is RETa3O9Ceramic, wherein RE consists of one or more of the rare earth elements.
Preferably, the heat insulation and temperature reduction layer is RE3TaO7Ceramic, wherein RE consists of one or more of the rare earth elements.
By adopting the method, the oxygen propagation resisting layer, the thermal expansion coefficient buffer layer and the heat insulation and temperature reduction layer are respectively rare earth tantalate (RETaO)4、RETa3O9And RE3TaO7They all have sufficient tantalum elements, ensure that the components cannot react with each other, and have excellent chemical compatibility with the oxygen barrier layer and the bonding layer; oxygen-propagation-blocking layer RETaO4The ceramic is defect-free lattice, has extremely weak oxygen ion propagation performance, can effectively prevent oxygen from propagating into the interior to react with the ceramic matrix, and simultaneously RETaO4The ceramic has a structure of compounding with a ceramic matrixClose thermal expansion coefficient (3-6X 10) of the materials-6K-1) The thermal stress generated by the thermal expansion coefficient difference is effectively reduced, and the service life of the coating is prolonged; preparing a thermal expansion coefficient buffer layer RETa between the heat insulation and temperature reduction layer and the oxygen transmission resisting layer3O9The ceramic effectively reduces the difference of the thermal expansion coefficients between the two layers, effectively reduces the thermal stress generated by the difference of the thermal expansion coefficients, and prolongs the service life of the coating; rare earth tantalate RETaO4、RETa3O9And RE3TaO7All have extremely low thermal conductivity, thereby providing excellent heat insulation and temperature reduction effects; meanwhile, the multilayer structure combined with the whole material system provides interface thermal resistance, so that the internal temperature of the unmanned aerial vehicle is further reduced, internal parts of the unmanned aerial vehicle can be guaranteed to be in service at the limit working temperature, and finally the fire rescue unmanned aerial vehicle can be used in a high-temperature environment for a long time.
The invention also provides a preparation method of the ceramic matrix composite system on the surface of the unmanned aerial vehicle, which comprises the following steps:
s1, preparing a bonding layer with the thickness of 100-200 mu m on the upper surface of the ceramic matrix composite substrate by using a cold spraying method;
s2: placing the bonding layer in S1 in air for oxidation to obtain an oxygen barrier layer with the thickness less than 1 μm;
s3: preparing an oxygen barrier propagation layer with the thickness of 30-50 mu m on the surface of the oxygen barrier layer in S2 by using an atmospheric plasma spraying method;
s4: preparing a buffer layer with the thermal expansion coefficient of 30-50 microns on the surface of the oxygen barrier propagation layer in the S3 by using an atmospheric plasma spraying method;
s5: and preparing the heat-insulating and temperature-reducing ceramic layer with the thickness of 100-1000 microns on the surface of the thermal expansion coefficient buffer layer in the step S4 by using an atmospheric plasma spraying method.
Preferably, in the cold spraying process in the step S1, compressed nitrogen is used as working gas, the spraying pressure is 0.66MPa, the spraying distance is 30mm, the spraying temperature is 800 ℃, and the powder feeding speed is 40 g/min; in the process of spraying the oxygen barrier propagation layer by using the atmospheric plasma spraying method in the S3, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 42kW during spraying, the distance of the spray gun is 100mm, the flow rates of argon and hydrogen are 40/12slpm and 45/10slpm respectively, the feeding speed is 50g/min, the speed of the spray gun is 300mm/S, and the spraying time is 1 min; in the process of spraying the thermal expansion coefficient buffer layer by using the atmospheric plasma spraying method in the S4, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the flow rates of the argon and the hydrogen are 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/S, and the spraying time is 2 min; the in-process of utilizing atmosphere plasma spraying method spraying thermal-insulated cooling ceramic layer among S5, utilize argon gas as protective gas, utilize hydrogen as combustion gas, wherein spray gun power is 46kW, and the spray gun distance is 150mm, and the gas flow of argon gas and hydrogen is 42/12slpm and 40/10slpm respectively, and the input speed is 30g/min, and the spray gun speed is 300mm/S, and the spraying time is 2 min.
In summary, compared with the prior art, the invention has the advantages that:
according to the technical scheme, the bonding layer, the oxidation resistant layer, the oxygen barrier layer, the thermal expansion coefficient buffer layer and the heat insulation and cooling layer are sequentially prepared on the surface of the ceramic matrix composite material, so that the effects of heat insulation and cooling, oxygen transmission resistance and oxidation resistance can be provided for the ceramic matrix composite material; meanwhile, the existence of the thermal expansion coefficient buffer layer can effectively reduce the thermal expansion coefficient difference between the heat insulation and temperature reduction layer and the oxygen transmission resisting layer so as to reduce the thermal stress and prolong the service life of the coating system; when the material system is used as a fire rescue unmanned aerial vehicle body material, the advantage that the heat insulation and cooling effects are improved by using the low heat conductivity and the multilayer structure can ensure that the internal parts of the body are under the limit service temperature of the internal parts under the service environment of a fire scene, so that the internal parts can be effectively used for a long time.
Drawings
FIG. 1 is a schematic view of the structure of an unmanned aerial vehicle surface ceramic matrix composite system according to the present invention;
FIG. 2 is a graph showing the comparison of the thermal conductivity of the ceramic matrix composite system and the surface heat insulating and temperature reducing layer prepared according to the present invention;
FIG. 3 is a drawing of a surface coating of a ceramic matrix composite system prepared in accordance with the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
Example 1:
the invention provides a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof. Referring to FIG. 1, according to an embodiment of the present invention, the silicon carbide fiber reinforced silicon carbide ceramic matrix is included, on which a bonding layer with a thickness of 100 μm, an oxygen barrier layer with a thickness less than 1 μm, an oxygen propagation barrier layer with a thickness of 30 μm, a thermal expansion coefficient buffer layer with a thickness of 30 μm, and a heat insulation and temperature reduction layer with a thickness of 100m are sequentially deposited; adopting metal tantalum Ta as a material of a bonding layer; the oxygen transmission resisting layer adopts rare earth tantalate RETaO4A ceramic coating, wherein RE is Yb; the thermal expansion coefficient buffer layer adopts RETa3O9Ceramic, wherein RE is Tm.
The method specifically comprises the following steps: (1) preparing a tantalum Ta bonding layer with the thickness of 100 mu m on the upper surface of the silicon carbide fiber reinforced silicon carbide substrate by using a cold spraying method; in the cold spraying process, compressed nitrogen is used as working gas, the spraying pressure is 0.66MPa, the spraying distance is 30mm, the spraying temperature is 800 ℃, and the powder feeding speed is 40 g/min; after the material sprayed with the tantalum Ta bonding layer is placed in the air, the metal tantalum is oxidized to form compact tantalum oxide Ta with the thickness of less than 1 mu m on the surface of the metal tantalum2O5An oxygen barrier layer.
(2) Compacting tantalum oxide Ta2O5Preparing an oxygen transmission resisting layer YbTaO with the thickness of 30 microns on the surface of the oxygen resisting layer by an atmospheric plasma spraying method4And (3) coating the ceramic. First using Yb2O3And Ta2O5Preparing spherical YbTaO by high-temperature solid-phase method4Spherical powder; benefit toIn the process of spraying the oxygen barrier propagation layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 42kW during spraying, the distance of the spray gun is 100mm, the flow rates of the argon and the hydrogen are 40/12slpm and 45/10slpm respectively, the feeding speed is 50g/min, the speed of the spray gun is 300mm/s, and the spraying time is 1 min.
(3) By atmospheric plasma spraying on YbTaO4Preparation of 30-micron-thick thermal expansion coefficient buffer layer TmTa on surface of ceramic oxygen barrier propagation layer3O9And (3) coating the ceramic. First using Tm2O3And Ta2O5Preparing spherical TmTa serving as a raw material by a high-temperature solid-phase method3O9Spherical powder; in the process of spraying the thermal expansion coefficient buffer layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the flow rates of the argon and the hydrogen are 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
(4) By atmospheric plasma spraying at TmTa3O9Preparing a heat-insulating and temperature-reducing ceramic layer Tm with the thickness of 200 microns on the surface of the ceramic thermal expansion coefficient buffer layer3TaO7And (3) coating the ceramic. First using Tm2O3And Ta2O5Preparing spherical Tm by high-temperature solid-phase method3TaO7Spherical powder; in the process of spraying the heat-insulating and cooling ceramic layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the gas flow of the argon and the hydrogen is 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
Example 2:
the invention provides a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof. Referring to FIG. 1, according to an embodiment of the present invention, a ceramic matrix composite substrate, silicon carbide fiber reinforced carbon, is providedThe body is sequentially deposited with a bonding layer with the thickness of 200 mu m, an oxygen barrier layer with the thickness less than 1 mu m, an oxygen propagation barrier layer with the thickness of 50 mu m, a thermal expansion coefficient buffer layer with the thickness of 50 mu m and a heat insulation and temperature reduction layer with the thickness of 100 m; adopting metal tantalum Ta as a material of a bonding layer; the oxygen transmission resisting layer adopts rare earth tantalate RETaO4The ceramic coating, wherein RE is Yb and Lu; the thermal expansion coefficient buffer layer adopts RETa3O9Ceramic, wherein RE is La, Ho and Tm.
The method specifically comprises the following steps: (1) preparing a tantalum Ta bonding layer with the thickness of 200 mu m on the upper surface of the silicon carbide fiber reinforced silicon carbide substrate by using a cold spraying method; in the cold spraying process, compressed nitrogen is used as working gas, the spraying pressure is 0.66MPa, the spraying distance is 30mm, the spraying temperature is 800 ℃, and the powder feeding speed is 40 g/min; after the material sprayed with the tantalum Ta bonding layer is placed in the air, the metal tantalum is oxidized to form compact tantalum oxide Ta with the thickness of less than 1 mu m on the surface of the metal tantalum2O5An oxygen barrier layer.
(2) Compacting tantalum oxide Ta2O5Preparing oxygen-barrier propagation layer Yb with thickness of 50 microns on the surface of the oxygen-barrier layer by using an atmospheric plasma spraying method1/2Lu1/2TaO4And (3) coating the ceramic. First use Lu2O3、Yb2O3And Ta2O5Preparing spherical Yb from the raw material by a high-temperature solid-phase method1/2Lu1/2TaO4Spherical powder; in the process of spraying the oxygen-blocking propagation layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 42kW during spraying, the distance of the spray gun is 100mm, the flow rates of the argon and the hydrogen are 40/12slpm and 45/10slpm respectively, the feeding speed is 50g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
(3) By atmospheric plasma spraying on Yb1/2Lu1/2TaO4Preparation of 50-micrometer-thick buffer layer La with thermal expansion coefficient on surface of oxygen-resistant ceramic propagation layer1/3Ho1/3Tm1/3Ta3O9And (3) coating the ceramic. First, La was used2O3、Ho2O3、Tm2O3And Ta2O5Preparing spherical La by high-temperature solid-phase method1/3Ho1/3Tm1/3Ta3O9Spherical powder; in the process of spraying the thermal expansion coefficient buffer layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the flow rates of the argon and the hydrogen are 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 3 min.
(4) By atmospheric plasma spraying, in La1/3Ho1/3Tm1/3Ta3O9Preparing a heat-insulating and temperature-reducing ceramic layer Y with the thickness of 100 microns on the surface of the ceramic thermal expansion coefficient buffer layer3TaO7And (3) coating the ceramic. First using Y2O3And Ta2O5Preparing spherical Y from raw materials by a high-temperature solid-phase method3TaO7Spherical powder; in the process of spraying the heat-insulating and cooling ceramic layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the gas flow of the argon and the hydrogen is 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
Example 3:
the invention provides a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof. Referring to FIG. 1, according to an embodiment of the present invention, the carbon fiber reinforced silicon carbide ceramic matrix comprises a carbon fiber reinforced silicon carbide substrate, on which an adhesion layer with a thickness of 150 μm, an oxygen barrier layer with a thickness of less than 1 μm, an oxygen propagation barrier layer with a thickness of 35 μm, a thermal expansion coefficient buffer layer with a thickness of 35 μm, and a thermal insulation and cooling layer with a thickness of 1000 μm are sequentially deposited; adopting metal tantalum Ta as a material of a bonding layer; the oxygen transmission resisting layer adopts rare earth tantalate RETaO4A ceramic coating, wherein RE is Sc; the thermal expansion coefficient buffer layer adopts RETa3O9Ceramic, wherein RE is La.
The method specifically comprises the following steps: (1) by means of cold sprayingPreparing a tantalum Ta bonding layer with the thickness of 150 mu m on the upper surface of the silicon carbide fiber reinforced silicon carbide substrate; in the cold spraying process, compressed nitrogen is used as working gas, the spraying pressure is 0.66MPa, the spraying distance is 30mm, the spraying temperature is 800 ℃, and the powder feeding speed is 40 g/min; after the material sprayed with the tantalum Ta bonding layer is placed in the air, the metal tantalum is oxidized to form compact tantalum oxide Ta with the thickness of less than 1 mu m on the surface of the metal tantalum2O5An oxygen barrier layer.
(2) Compacting tantalum oxide Ta2O5Preparing an oxygen transmission resisting layer ScTaO with the thickness of 35 microns on the surface of the oxygen resistance layer by an atmospheric plasma spraying method4And (3) coating the ceramic. First using Sc2O3And Ta2O5Preparing spherical ScTaO serving as raw material by a high-temperature solid-phase method4Spherical powder; in the process of spraying the oxygen-blocking propagation layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 42kW during spraying, the distance of the spray gun is 100mm, the flow rates of the argon and the hydrogen are 40/12slpm and 45/10slpm respectively, the feeding speed is 50g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
(3) By atmospheric plasma spraying on ScTaO4Preparing 35-micron-thick thermal expansion coefficient buffer layer LaTa on surface of ceramic oxygen-barrier propagation layer3O9And (3) coating the ceramic. First, La was used2O3And Ta2O5Preparing spherical LaTa from the raw material by a high-temperature solid-phase method3O9Spherical powder; in the process of spraying the thermal expansion coefficient buffer layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the flow rates of the argon and the hydrogen are 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 3 min.
(4) By atmospheric plasma spraying on LaTa3O9Preparing a heat-insulating and temperature-reducing ceramic layer YLaDyTaO with the thickness of 1000 microns on the surface of the ceramic thermal expansion coefficient buffer layer7And (3) coating the ceramic. First using Y2O3、La2O3、Dy2O3And Ta2O5Preparing spherical YLaDyTaO by high-temperature solid-phase method7Spherical powder; in the process of spraying the heat-insulating and cooling ceramic layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the gas flow of the argon and the hydrogen is 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 10 min.
Example 4:
the invention provides a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof. Referring to FIG. 1, according to an embodiment of the present invention, a carbon fiber reinforced carbon ceramic matrix is included, on which an adhesive layer having a thickness of 170 μm, an oxygen barrier layer having a thickness of less than 1 μm, an oxygen propagation barrier layer having a thickness of 35 μm, a thermal expansion coefficient buffer layer having a thickness of 40 μm, and a heat insulating and cooling layer having a thickness of 500m are sequentially deposited; adopting metal tantalum Ta as a material of a bonding layer; the oxygen transmission resisting layer adopts rare earth tantalate RETaO4The ceramic coating, wherein RE is Sc, Yb and Lu; the thermal expansion coefficient buffer layer adopts RETa3O9Ceramic, wherein RE is La, Ho, Er and Tm.
The method specifically comprises the following steps: (1) preparing a tantalum Ta bonding layer with the thickness of 170 mu m on the upper surface of the silicon carbide fiber reinforced silicon carbide substrate by using a cold spraying method; in the cold spraying process, compressed nitrogen is used as working gas, the spraying pressure is 0.66MPa, the spraying distance is 30mm, the spraying temperature is 800 ℃, and the powder feeding speed is 40 g/min; after the material sprayed with the tantalum Ta bonding layer is placed in the air, the metal tantalum is oxidized to form compact tantalum oxide Ta with the thickness of less than 1 mu m on the surface of the metal tantalum2O5An oxygen barrier layer.
(2) Compacting tantalum oxide Ta2O5Preparing an oxygen transmission barrier layer Sc with the thickness of 35 microns on the surface of the oxygen barrier layer by an atmospheric plasma spraying method1/3Yb1/3Lu1/3TaO4And (3) coating the ceramic. First using Sc2O3、Lu2O3、Yb2O3And Ta2O5Preparing spherical Sc serving as a raw material by a high-temperature solid-phase method1/3Yb1/3Lu1/3TaO4Spherical powder; in the process of spraying the oxygen-blocking propagation layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 42kW during spraying, the distance of the spray gun is 100mm, the flow rates of the argon and the hydrogen are 40/12slpm and 45/10slpm respectively, the feeding speed is 50g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
(3) By atmospheric plasma spraying, in Sc1/3Yb1/3Lu1/3TaO4Preparing a thermal expansion coefficient buffer layer La with the thickness of 40 microns on the surface of the oxygen barrier propagation layer of the ceramic1/4Ho1/4Tm1/4Er1/4Ta3O9And (3) coating the ceramic. First, Er was used2O3、La2O3、Ho2O3、Tm2O3And Ta2O5Preparing spherical La by high-temperature solid-phase method1/4Ho1/4Tm1/4Er1/4Ta3O9Spherical powder; in the process of spraying the thermal expansion coefficient buffer layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the flow rates of the argon and the hydrogen are 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 3 min.
(4) By atmospheric plasma spraying, in La1/4Ho1/4Tm1/4Er1/4Ta3O9Preparing a heat-insulating and temperature-reducing ceramic layer Y with the thickness of 500 microns on the surface of the ceramic thermal expansion coefficient buffer layer3TaO7And (3) coating the ceramic. First using Y2O3And Ta2O5Preparing spherical Y from raw materials by a high-temperature solid-phase method3TaO7Spherical powder; in the process of spraying the heat-insulating and temperature-reducing ceramic layer by using an atmospheric plasma spraying method, argon is used as protective gas, and hydrogen is used as combustion gas, whereinThe power of the spray gun is 46kW, the distance of the spray gun is 150mm, the gas flow rates of argon and hydrogen are 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 10 min.
Comparative example 1:
the invention provides a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof. Referring to FIG. 1, according to an embodiment of the present invention, a SiC carbon fiber reinforced ceramic matrix is included, on which a bonding layer with a thickness of 200 μm, an oxygen barrier layer with a thickness of less than 1 μm, an oxygen propagation barrier layer with a thickness of 50 μm, and a heat insulation and temperature reduction layer with a thickness of 100m are sequentially deposited; adopting metal tantalum Ta as a material of a bonding layer; the oxygen transmission resisting layer adopts rare earth tantalate RETaO4The ceramic coating, wherein RE is Yb and Lu; the thermal expansion coefficient buffer layer adopts RETa3O9Ceramic, wherein RE is La, Ho and Tm.
The method specifically comprises the following steps: (1) preparing a tantalum Ta bonding layer with the thickness of 200 mu m on the upper surface of the silicon carbide fiber reinforced silicon carbide substrate by using a cold spraying method; in the cold spraying process, compressed nitrogen is used as working gas, the spraying pressure is 0.66MPa, the spraying distance is 30mm, the spraying temperature is 800 ℃, and the powder feeding speed is 40 g/min; after the material sprayed with the tantalum Ta bonding layer is placed in the air, the metal tantalum is oxidized to form compact tantalum oxide Ta with the thickness of less than 1 mu m on the surface of the metal tantalum2O5An oxygen barrier layer.
(2) Compacting tantalum oxide Ta2O5Preparing oxygen-barrier propagation layer Yb with thickness of 50 microns on the surface of the oxygen-barrier layer by using an atmospheric plasma spraying method1/2Lu1/2TaO4And (3) coating the ceramic. First use Lu2O3、Yb2O3And Ta2O5Preparing spherical Yb from the raw material by a high-temperature solid-phase method1/2Lu1/2TaO4Spherical powder; utilize atmosphere plasma spraying method spraying to hinder the in-process of oxygen propagation layer, utilize argon gas as protective gas, utilize hydrogen as combustion gas, wherein, spray gun power is 42kW during the spraying, and the spray gun distance is 100mm, and the gas flow of argon gas and hydrogen is 40/12slpm and 45/10slpm respectively, and the feed rateThe degree is 50g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
(3) By atmospheric plasma spraying on the oxygen-barrier layer Yb1/2Lu1/2TaO4Preparing a heat-insulating and temperature-reducing ceramic layer Y with the thickness of 100 microns on the surface of the ceramic coating3TaO7And (3) coating the ceramic. First using Y2O3And Ta2O5Preparing spherical Y from raw materials by a high-temperature solid-phase method3TaO7Spherical powder; in the process of spraying the heat-insulating and cooling ceramic layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the gas flow of the argon and the hydrogen is 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
Comparative example 2:
the invention provides a ceramic matrix composite system on the surface of an unmanned aerial vehicle and a preparation method thereof. Referring to FIG. 1, according to an embodiment of the present invention, the carbon fiber reinforced silicon carbide ceramic matrix is provided, on which an oxygen propagation barrier layer with a thickness of 35 μm, a thermal expansion coefficient buffer layer with a thickness of 35 μm, and a thermal insulation and cooling layer with a thickness of 1000 μm are sequentially deposited; adopting metal tantalum Ta as a material of a bonding layer; the oxygen transmission resisting layer adopts rare earth tantalate RETaO4A ceramic coating, wherein RE is Sc; the thermal expansion coefficient buffer layer adopts RETa3O9Ceramic, wherein RE is La.
The method specifically comprises the following steps: (1) preparing an oxygen transmission resisting layer ScTaO with the thickness of 35 microns on the surface of a matrix by an atmospheric plasma spraying method4And (3) coating the ceramic. First using Sc2O3And Ta2O5Preparing spherical ScTaO serving as raw material by a high-temperature solid-phase method4Spherical powder; utilize atmosphere plasma spraying method spraying to hinder the in-process of oxygen propagation layer, utilize argon gas as protective gas, utilize hydrogen as combustion gas, wherein, spray gun power is 42kW during the spraying, and the spray gun distance is 100mm, and the gas flow of argon gas and hydrogen is 40/12slpm and 45/10slpm respectively, and the input speed is for50g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2 min.
(2) By atmospheric plasma spraying on ScTaO4Preparing 35-micron-thick thermal expansion coefficient buffer layer LaTa on surface of ceramic oxygen-barrier propagation layer3O9And (3) coating the ceramic. First, La was used2O3And Ta2O5Preparing spherical LaTa from the raw material by a high-temperature solid-phase method3O9Spherical powder; in the process of spraying the thermal expansion coefficient buffer layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the flow rates of the argon and the hydrogen are 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 3 min.
(3) By atmospheric plasma spraying on LaTa3O9Preparing a heat-insulating and temperature-reducing ceramic layer YLaDyTaO with the thickness of 1000 microns on the surface of the ceramic thermal expansion coefficient buffer layer7And (3) coating the ceramic. First using Y2O3、La2O3、Dy2O3And Ta2O5Preparing spherical YLaDyTaO by high-temperature solid-phase method7Spherical powder; in the process of spraying the heat-insulating and cooling ceramic layer by using an atmospheric plasma spraying method, argon is used as protective gas, hydrogen is used as combustion gas, wherein the power of a spray gun is 46kW, the distance of the spray gun is 150mm, the gas flow of the argon and the hydrogen is 42/12slpm and 40/10slpm respectively, the feeding speed is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 10 min.
The specific composition of the material system prepared in the above examples is shown in table 1. To characterize the performance of the examples and comparative examples, we tested the number of thermal cycles, oxidative weight loss, and adiabatic cooling gradients required for their failure. Wherein the thermal cycle test process is that the surface of the coating is heated to 1000 ℃ by flame and is kept warm for 3 minutes, and then is cooled for 2 minutes, and the cycle is carried out until the coating is peeled off or the oxidation weight loss of the material exceeds 10 percent; the weight loss rate of the material system before (W1) and after (W2) the total thermal cycle times (W1-W2)/W1 multiplied by 100% is oxidation weight loss rate; the temperature difference between the surface of the coating and the contact interface of the substrate and the coating in the first test is the thermal insulation gradient of the coating material, and the results are shown in table 2.
TABLE 1
Figure BDA0003311504950000141
TABLE 2
Number of thermal cycles Oxidation weight loss ratio (%) Heat insulation gradient (. degree. C.)
Example 1 303 12 482
Example 2 317 15 409
Example 3 1352 10 627
Example 4 1068 13 516
Comparative example 1 23 26 388
Comparative example 2 16 22 611
Test results show that the material for preparing the complete coating system has excellent heat insulation and cooling effects, and can be used for a long time in service at the temperature of 1000 ℃, so that the oxidation failure of the matrix material is prevented; the material which is not prepared into a complete coating system fails early due to large difference of thermal expansion coefficients and weak binding force, so that the service requirement cannot be met.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.

Claims (10)

1.一种无人机表面的陶瓷基复合材料体系，包括陶瓷基复合材料基体，其特征在于：所述陶瓷基复合材料基体覆于飞行器机身表面，在所述陶瓷基复合材料基体上依次制备有粘结层、阻氧层、阻氧传播层、热膨胀系数缓冲层和隔热降温层；其中，所述粘结层的厚度为100-200μm，所述阻氧传播层的厚度为30-50μm，所述热膨胀系数缓冲层的厚度为30-50μm，所述隔热降温层的厚度为100-1000μm。1. a ceramic matrix composite material system on the surface of an unmanned aerial vehicle, comprising a ceramic matrix composite material matrix, characterized in that: the ceramic matrix composite material matrix is covered on the surface of the aircraft fuselage, and sequentially on the ceramic matrix composite material matrix An adhesive layer, an oxygen barrier layer, an oxygen barrier propagation layer, a thermal expansion coefficient buffer layer and a thermal insulation and cooling layer are prepared; wherein, the thickness of the adhesive layer is 100-200 μm, and the thickness of the oxygen barrier layer is 30- 50 μm, the thickness of the thermal expansion coefficient buffer layer is 30-50 μm, and the thickness of the thermal insulation and cooling layer is 100-1000 μm. 2.根据权利要求1所述的一种无人机表面的陶瓷基复合材料体系，其特征在于，所述阻氧传播层的热膨胀系数为3-6×10-6K-1，所述热膨胀系数缓冲层的热膨胀系数为6-9×10- 6K-1，所述隔热降温层的热膨胀系数为9-11×10-6K-1。2 . The ceramic matrix composite material system on the surface of a drone according to claim 1 , wherein the thermal expansion coefficient of the oxygen propagation barrier layer is 3-6×10 -6 K -1 . The coefficient of thermal expansion of the coefficient buffer layer is 6-9 ×10 -6 K -1 , and the coefficient of thermal expansion of the thermal insulation and cooling layer is 9-11×10 -6 K -1 . 3.根据权利要求2所述的一种无人机表面的陶瓷基复合材料体系，其特征在于，所述陶瓷基复合材料基体为碳化硅纤维增强碳化硅、碳纤维增强碳、碳纤维增强碳化硅和碳化硅纤维增强碳中的一种。3. The ceramic matrix composite material system of a kind of unmanned aerial vehicle surface according to claim 2, is characterized in that, described ceramic matrix composite material matrix is silicon carbide fiber reinforced silicon carbide, carbon fiber reinforced carbon, carbon fiber reinforced silicon carbide and A type of silicon carbide fiber reinforced carbon. 4.根据权利要求2所述的一种无人机表面的陶瓷基复合材料体系，其特征在于，所述粘结层为通过冷喷涂方法将Ta材料喷涂于陶瓷基复合材料基体表面。4 . The ceramic matrix composite material system on the surface of a UAV according to claim 2 , wherein the bonding layer is formed by spraying the Ta material on the surface of the ceramic matrix composite material by a cold spray method. 5 . 5.根据权利要求2所述的一种无人机表面的陶瓷基复合材料体系，其特征在于，所述阻氧层为Ta2O5。5 . The ceramic matrix composite material system of claim 2 , wherein the oxygen barrier layer is Ta 2 O 5 . 6 . 6.根据权利要求2所述的一种无人机表面的陶瓷基复合材料体系，其特征在于，所述阻氧传播层为稀土钽酸盐RETaO4陶瓷涂层；其中，RE由稀土元素中的一种或者多种组成。6 . The ceramic matrix composite material system on the surface of a drone according to claim 2 , wherein the oxygen barrier layer is a rare earth tantalate RETaO 4 ceramic coating; wherein, RE is composed of rare earth elements. 7 . one or more components. 7.根据权利要求2所述的一种无人机表面的陶瓷基复合材料体系，其特征在于，所述热膨胀系数缓冲层为RETa3O9陶瓷，其中RE由稀土元素中的一种或者多种组成。7 . The ceramic matrix composite material system on the surface of a drone according to claim 2 , wherein the thermal expansion coefficient buffer layer is RETa 3 O 9 ceramics, wherein RE is composed of one or more rare earth elements. 8 . species composition. 8.根据权利要求2所述的一种无人机表面的陶瓷基复合材料体系，其特征在于，所述隔热降温层为RE3TaO7陶瓷，其中RE由稀土元素中的一种或者多种组成。8 . The ceramic matrix composite material system on the surface of a drone according to claim 2 , wherein the thermal insulation and cooling layer is RE 3 TaO 7 ceramics, wherein RE is composed of one or more rare earth elements. 9 . species composition. 9.根据权利要求1-8任意一项所述的一种无人机表面的陶瓷基复合材料体系的制备方法，其特征在于，包括以下步骤：9. the preparation method of the ceramic matrix composite material system of a kind of unmanned aerial vehicle surface according to any one of claim 1-8, is characterized in that, comprises the following steps: S1:利用冷喷涂方法在陶瓷基复合材料基体上表面制备厚度为100-200μm的粘结层；S1: using a cold spray method to prepare a bonding layer with a thickness of 100-200 μm on the upper surface of the ceramic matrix composite material; S2：将S1中所述的粘结层放置在空气中进行氧化即获得厚度小于1μm的阻氧层；S2: The adhesive layer described in S1 is placed in the air for oxidation to obtain an oxygen barrier layer with a thickness of less than 1 μm; S3：利用大气等离子喷涂法将S2中所述的阻氧层表面制备厚度为30-50μm的阻氧传播层；S3: using atmospheric plasma spraying to prepare an oxygen barrier layer with a thickness of 30-50 μm on the surface of the oxygen barrier layer described in S2; S4：利用大气等离子喷涂法将S3中所述的阻氧传播层表面制备厚度为30-50微米的热膨胀系数缓冲层；S4: prepare a thermal expansion coefficient buffer layer with a thickness of 30-50 microns on the surface of the oxygen barrier layer described in S3 by atmospheric plasma spraying; S5：利用大气等离子喷涂法将S4中所述的热膨胀系数缓冲层表面制备厚度为100-1000微米的隔热降温陶瓷层。S5: Prepare a thermal insulation and cooling ceramic layer with a thickness of 100-1000 microns on the surface of the thermal expansion coefficient buffer layer described in S4 by using the atmospheric plasma spraying method. 10.根据权利要求9所述的一种无人机表面的陶瓷基复合材料体系的制备方法，其特征在于，所述S1中的冷喷涂方法喷涂过程中，以压缩氮气作为工作气体，喷涂压力0.66MPa，喷涂距离30mm，喷涂温度为800℃，送粉速率为40g/min；所述S3中的利用大气等离子喷涂法喷涂阻氧传播层的过程中，利用氩气作为保护气体，利用氢气作为燃烧气体，其中，喷涂时喷枪功率为42kW，喷枪距离为100mm，氩气和氢气的气流量分别为40/12slpm和45/10slpm，进料速度为50g/min，喷枪速度为300mm/s，喷涂时间为1min；所述S4中的利用大气等离子喷涂法喷涂热膨胀系数缓冲层的过程中，利用氩气作为保护气体，利用氢气作为燃烧气体，其中，喷枪功率为46kW，喷枪距离为150mm，氩气和氢气的气流量分别为42/12slpm和40/10slpm，进料速度为30g/min，喷枪速度为300mm/s，喷涂时间为2min；所述S5中的利用大气等离子喷涂法喷涂隔热降温陶瓷层的过程中，利用氩气作为保护气体，利用氢气作为燃烧气体，其中喷枪功率为46kW，喷枪距离为150mm，氩气和氢气的气流量分别为42/12slpm和40/10slpm，进料速度为30g/min，喷枪速度为300mm/s，喷涂时间为2min。10. the preparation method of the ceramic matrix composite material system of a kind of unmanned aerial vehicle surface according to claim 9, is characterized in that, in the cold spraying method spraying process in described S1, with compressed nitrogen as working gas, spraying pressure 0.66MPa, the spraying distance is 30mm, the spraying temperature is 800°C, and the powder feeding rate is 40g/min; in the process of spraying the oxygen propagation barrier layer by the atmospheric plasma spraying method in S3, argon is used as the protective gas, and hydrogen is used as the protective gas. Combustion gas, among them, the spray gun power is 42kW, the spray gun distance is 100mm, the gas flow rates of argon and hydrogen are 40/12slpm and 45/10slpm respectively, the feed rate is 50g/min, the spray gun speed is 300mm/s, and the spraying rate is 300mm/s. Time is 1min; in the process of utilizing atmospheric plasma spraying method to spray thermal expansion coefficient buffer layer in described S4, utilize argon gas as protective gas, utilize hydrogen as combustion gas, wherein, spray gun power is 46kW, spray gun distance is 150mm, argon gas and the gas flow of hydrogen are respectively 42/12slpm and 40/10slpm, the feed rate is 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2min; the use of atmospheric plasma spraying in the described S5 sprays thermal insulation and cooling ceramics In the process of layering, argon gas was used as protective gas, and hydrogen gas was used as combustion gas, wherein the power of the spray gun was 46kW, the distance of the spray gun was 150mm, the gas flow rates of argon gas and hydrogen gas were 42/12slpm and 40/10slpm respectively, and the feed rate was 30g/min, the speed of the spray gun is 300mm/s, and the spraying time is 2min.
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