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Preparation method of composite ceramic material for thermal protection connection

A composite ceramic and thermal protection technology, applied in the field of ceramic materials, can solve problems such as poor reliability, and achieve the effects of good self-lubrication, good hardness and bearing capacity, and low diffusion coefficient

Inactive Publication Date: 2020-01-10
曾军
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] The technical problem to be solved by the present invention: Aiming at the problem of obvious brittleness of traditional ceramic materials and poor reliability when used for high temperature connection, a preparation method of composite ceramic material for thermal protection connection is provided

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] In terms of parts by weight, weigh 30 parts of silicon dioxide powder and 60 parts of carbon powder respectively, place the silicon dioxide powder and carbon powder in a mixer, and stir at a speed of 180r / min for 20min at room temperature to obtain a mixed powder. The powder is placed in a tube-type atmosphere furnace, nitrogen gas is introduced at a flow rate of 100mL / min, and the temperature is raised from room temperature to 1500°C under a power of 8kW, kept for calcination for 1h, and cooled to room temperature with the furnace to obtain a reaction powder. In a muffle furnace, raise the temperature from room temperature to 600°C at a rate of 5°C / min, heat-preserve and calcinate for 40 minutes, and cool to room temperature with the furnace to obtain silicon nitride powder; then weigh 40 parts by weight of oxygen Zirconium chloride, 48 parts of ethyl orthosilicate, 16 parts of ammonia water with a mass concentration of 1%, 240 parts of deionized water, zirconium oxychl...

Embodiment 2

[0039] In terms of parts by weight, weigh 35 parts of silicon dioxide powder and 70 parts of carbon powder respectively, place the silicon dioxide powder and carbon powder in a mixer, and stir for 25 minutes at a speed of 190 r / min at room temperature to obtain a mixed powder. The powder is placed in a tube-type atmosphere furnace, nitrogen gas is introduced at a gas flow rate of 110mL / min, the temperature is raised from room temperature to 1550°C under the power of 9kW, heat preservation and calcination is carried out for 1h, and the reaction powder is obtained by cooling to room temperature with the furnace. In a muffle furnace, raise the temperature from room temperature to 700°C at a rate of 5°C / min, keep the temperature for calcination for 50 minutes, and cool down to room temperature with the furnace to obtain silicon nitride powder; then weigh 45 parts of oxygen by weight. Zirconium chloride, 54 parts of ethyl orthosilicate, 18 parts of ammonia water with a mass concentr...

Embodiment 3

[0041] In terms of parts by weight, weigh 40 parts of silicon dioxide powder and 80 parts of carbon powder respectively, put the silicon dioxide powder and carbon powder in a mixer, and stir at a speed of 200r / min for 30min at room temperature to obtain a mixed powder. The powder is placed in a tubular atmosphere furnace, fed with nitrogen gas at a gas flow rate of 120mL / min, raised from room temperature to 1600°C under a power of 10kW, kept for calcination for 2 hours, and cooled to room temperature with the furnace to obtain a reaction powder, which is placed in a In a muffle furnace, raise the temperature from room temperature to 800°C at a rate of 5°C / min, heat-preserve and calcinate for 60 minutes, and cool down to room temperature with the furnace to obtain silicon nitride powder; then weigh 50 parts by weight of oxygen Zirconium chloride, 60 parts of ethyl orthosilicate, 20 parts of ammonia water with a mass concentration of 1%, 300 parts of deionized water, zirconium ox...

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Abstract

The invention relates to a preparation method of a composite ceramic material for thermal protection connection, and belongs to the technical field of ceramic materials. According to the preparation method, silicon nitride is used as a raw material to prepare the composite ceramic material for thermal protection connection; silicon nitride has the advantages of hardness, heat resistance, wear resistance and corrosion resistance of a common ceramic material and has the advantages of good thermal shock resistance, high-temperature creep resistance, good self-lubricating property, good chemical stability and the like, and has excellent dielectric properties such as relatively low density, low dielectric constant, low dielectric loss and the like; the electronegativity of silicon and nitrogenelements in silicon nitride is similar; the steam pressure is high; the diffusion coefficient is very low; silicon nitride is a covalent compound with high bond strength and can form oxide protectivefilms in air, so that good chemical stability is achieved; the reliability of the composite ceramic material for thermal protection connection can be effectively improved by taking silicon carbide asa raw material, and the composite ceramic material for thermal protection connection has good hardness and bearing capacity.

Description

technical field [0001] The invention relates to a preparation method of a composite ceramic material for thermal protection connection, belonging to the technical field of ceramic materials. Background technique [0002] The reuse of spacecraft can effectively reduce the transportation cost of the space-to-earth transportation system and improve operational efficiency. It will be used more and more in the aerospace field in the future. The reusable spacecraft must pass through the atmosphere at a very high speed in the process of going back and forth between space and the earth. During the passage, the surface of the spacecraft will have strong friction with the surrounding atmosphere, which will generate a lot of heat. The surface temperature can reach Thousands of degrees Celsius. Therefore, a thermal protection system (TPS) will be installed on the surface of the spacecraft to reduce aerodynamic heat from entering the interior of the body, so as to protect the normal ope...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/584C04B35/626C04B35/622C04B35/80
CPCC04B35/584C04B35/622C04B35/626C04B35/6265C04B35/62675C04B35/6268C04B2235/3206C04B2235/3208C04B2235/3248C04B2235/3418C04B2235/422C04B2235/5248C04B2235/6562C04B2235/6567C04B2235/667C04B2235/96C04B2235/9607
Inventor 曾军
Owner 曾军
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