Ceramic matrix composite material and preparation method thereof

A composite material and ceramic-based technology, applied in the field of composite materials, to achieve the effects of good toughness, uniform distribution, and outstanding high-temperature mechanical properties

Active Publication Date: 2019-07-19
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, there have been no reports on the modification of carbon / silicon carbide and other composite materials by hafnium-tantalum solid solution. The reason may be that based on the characteristics of hafnium-tantalum solid solution, there is no suitable process to uniformly disperse hafnium-tantalum solid solution in silicon carbide.

Method used

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  • Ceramic matrix composite material and preparation method thereof

Examples

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Effect test

Embodiment 1

[0050] A method for preparing a carbon / hafnium-tantalum solid solution-silicon carbide ultra-high temperature ceramic matrix composite material, the specific steps are:

[0051] 1) The needle-punched carbon fiber reinforcement was treated at a high temperature of 1700°C for 2 hours, and then deposited in a vapor deposition furnace for 150 hours, 120 hours, and 100 hours respectively, so that the density of the fiber reinforcement reached 1.10 g / cm 3 ;

[0052] 2) 5 kilograms of hafnium-tantalum copolymer resin, 1 kilogram of polycarbosilane and 6 kilograms of allylphenol were mechanically stirred for 5 hours, and after standing for 10 hours, a hafnium-tantalum-silicon ternary composite ceramic precursor solution was prepared;

[0053] 3) Immerse the fiber reinforcement obtained in 1) in the precursor solution of 2), and the immersion conditions are: immersion in a vacuum of 100KPa for 2 hours, and then immersion in a pressure of 3MPa for 2 hours. Finally, further pressurize t...

Embodiment 2

[0062] A method for preparing a carbon / hafnium-tantalum solid solution-silicon carbide ultra-high temperature ceramic matrix composite material, the specific steps are:

[0063] 1) Treat the stitched carbon fiber reinforcement at a high temperature of 1700°C for 2 hours, and then deposit it in a vapor deposition furnace for 150 hours, 100 hours, and 100 hours respectively, so that the density of the fiber reinforcement reaches 1.20 g / cm 3 ;

[0064] 2) 5 kilograms of hafnium-tantalum copolymer resin, 1 kilogram of polycarbosilane and 6 kilograms of allylphenol were mechanically stirred for 5 hours, and after standing for 10 hours, a hafnium-tantalum-silicon ternary composite ceramic precursor solution was prepared;

[0065] 3) Immerse the fiber reinforcement obtained in 1) in the precursor solution of 2), and the immersion conditions are: immersion in a vacuum of 100KPa for 2 hours, and then immersion in a pressure of 3MPa for 2 hours. Finally, further pressurize to 10MPa, he...

Embodiment 3

[0074] A method for preparing a carbon / hafnium-tantalum solid solution-silicon carbide ultra-high temperature ceramic matrix composite material, the specific steps are:

[0075] 1) Treat the finely woven and punctured carbon fiber reinforcement at a high temperature of 1700°C for 2 hours, and then deposit it in a vapor deposition furnace for 150 hours, 100 hours, and 100 hours respectively, so that the density of the fiber reinforcement reaches 1.23g / cm 3 ;

[0076] 2) 5 kilograms of hafnium-tantalum copolymer resin, 1 kilogram of polycarbosilane and 6 kilograms of allylphenol were mechanically stirred for 5 hours, and after standing for 10 hours, a hafnium-tantalum-silicon ternary composite ceramic precursor solution was prepared;

[0077] 3) Immerse the fiber reinforcement obtained in 1) in the precursor solution of 2), and the immersion conditions are: immersion in a vacuum of 100KPa for 2 hours, and then immersion in a pressure of 3MPa for 2 hours. Finally, further pressu...

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Abstract

The invention provides a ceramic matrix composite material and a preparation method thereof, wherein a carbon fiber preform is used as a skeleton, and is immersed in a hafnium-tantalum-silicon ternarycomposite phose ceramic precursor solution, and curing and cracking are performed to prepare the composite material. According to the preparation method, a pyrolytic carbon interface layer is prepared on a carbon fiber preform by using a chemical vapor infiltration method, matrix densification treatment is performed by using a hafnium-tantalum-silicon ternary composite phose ceramic precursor impregnation cracking method, and finally pore sealing treatment is performed by using a chemical vapor infiltration method. According to the present invention, the method has characteristics of simple process and short development period; and the prepared ultra-high temperature ceramic matrix composite material has the uniform distribution of various components of the matrix, has characteristics ofultra-high-temperature resistance, oxidation resistance and ablation resistance, can be used as the high temperature thermal structure material for hypersonic vehicles and rocket propulsion systems, and has broad application prospects.

Description

technical field [0001] The invention relates to a ceramic-based composite material and a preparation method thereof, in particular to a carbon / hafnium-tantalum solid solution-silicon carbide ceramic-based composite material and a preparation method thereof, belonging to the technical field of composite materials. Background technique [0002] Carbon fiber toughened silicon carbide ceramic matrix composites (C f / SiC composite material) is a high-performance thermal structural material. It overcomes the Achilles heel of brittleness of single-phase ceramic materials, and has excellent characteristics such as low density, high temperature resistance, high strength, oxidation resistance and ablation resistance. The rudder has been applied. However, long-term research has shown that traditional C f The long-term anti-oxidation service temperature of SiC composite materials does not exceed 1650 °C. When the Mach number of a hypersonic vehicle exceeds 6, its high-temperature st...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/56C04B35/622C04B41/87
CPCC04B35/806C04B35/5607C04B35/622C04B41/5059C04B41/87C04B2235/3826C04B2235/77C04B2235/96C04B2235/9607C04B2235/9684C04B41/4529
Inventor 裴雨辰刘伟
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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