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Cf/MC-SiC composite material and preparation method thereof

A composite material, MC-C technology, applied in ceramic products, other household utensils, applications, etc., can solve the problems of high material porosity, long preparation cycle, etc., and achieve the effect of low pressure, excellent thermal conductivity, and easy operation

Active Publication Date: 2016-10-12
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there are also disadvantages such as high material porosity and long preparation cycle.

Method used

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  • Cf/MC-SiC composite material and preparation method thereof
  • Cf/MC-SiC composite material and preparation method thereof
  • Cf/MC-SiC composite material and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0034] A Cf / ZrC-SiC composite material of the present invention includes a carbon fiber preform, a ZrC matrix and a SiC matrix, and the ZrC matrix and the SiC matrix are uniformly filled in the pores of the carbon fiber preform. In the Cf / ZrC-SiC composite material, ZrC The volume fraction of the matrix is ​​10%, the volume fraction of the SiC matrix is ​​30%, and the porosity is 6%.

[0035] A kind of preparation method of the Cf / ZrC-SiC composite material of above-mentioned present embodiment, comprises the following steps:

[0036] (1) Preparation of ZrC ceramic precursor solution:

[0037] ZrOCl with a molar ratio of 1:0.5:0.5:60 2 ·8H 2 O, citric acid monohydrate, ethylene glycol and distilled water are mixed and stirred and dissolved at room temperature, after the dissolution is completed, the ZrC ceramic precursor solution is prepared;

[0038] (2) Preparing Cf / ZrC biscuit by impregnating and cracking the precursor:

[0039] (2.1) Using the chemical vapor deposition...

Embodiment 2

[0046] A Cf / ZrC-SiC composite material of the present invention includes a carbon fiber preform, a ZrC matrix and a SiC matrix, and the ZrC matrix and the SiC matrix are uniformly filled in the pores of the carbon fiber preform. In the Cf / ZrC-SiC composite material, ZrC The volume fraction of the matrix is ​​17%, the volume fraction of the SiC matrix is ​​25%, and the porosity is 2%.

[0047] A kind of preparation method of the Cf / ZrC-SiC composite material of above-mentioned present embodiment, comprises the following steps:

[0048] (1) Preparation of ZrC ceramic precursor solution:

[0049] ZrOCl with a molar ratio of 1:6:10:600 2 ·8H 2 O, citric acid monohydrate, ethylene glycol and distilled water are mixed and stirred and dissolved at room temperature, after the dissolution is completed, the ZrC ceramic precursor solution is prepared;

[0050] (2) Preparing Cf / ZrC biscuit by impregnating and cracking the precursor:

[0051] (2.1) Using chemical vapor deposition proce...

Embodiment 3

[0070] A Cf / HfC-SiC composite material of the present invention comprises a carbon fiber preform, an HfC matrix and a SiC matrix, the HfC matrix and the SiC matrix are evenly filled in the pores of the carbon fiber preform, and in the Cf / HfC-SiC composite material, the HfC The volume fraction of the matrix is ​​14%, the volume fraction of the SiC matrix is ​​27%, and the porosity is 5%.

[0071] A kind of preparation method of the Cf / HfC-SiC composite material of above-mentioned present embodiment, comprises the following steps:

[0072] (1) Preparation of HfC ceramic precursor solution:

[0073] HfOCl with a molar ratio of 1:1:3:100 2 ·8H 2 O, citric acid monohydrate, ethylene glycol and distilled water are mixed and stirred and dissolved at room temperature, after the dissolution is completed, the HfC ceramic precursor solution is prepared;

[0074] (2) Preparing Cf / HfC biscuit by impregnating and cracking the precursor:

[0075] (2.1) Using the chemical vapor deposition...

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Abstract

The invention discloses a Cf / MC-SiC composite material and a preparation method thereof. The Cf / MC-SiC composite material comprises a carbon fiber fabricated part, an MC substrate and an SiC substrate, wherein M is Zr or Hf, the MC substrate and the SiC substrate are uniformly filled in the holes of the carbon fiber fabricated part, in the Cf / MC-SiC composite material, the volume fraction of the MC substrate is 10%-20%, the volume fraction of the SiC substrate is 20%-30%, and the percentage of opening of 2%-10%. The preparation method comprises the following steps that (1) a precursor is soaked and split for preparing a Cf / MC blank; (2) a Cf / MC-C blank is prepared; (3) the Cf / MC-SiC composite material is prepared with a gas phase siliconizing method. The Cf / MC-SiC composite material has the advantages that the material is high in content of MC substrate, low in porosity, high in heat conductivity, excellent in oxidation resistance, ablation resistance and mechanical property and the like, and the preparation method is simple in technology and easy to implement.

Description

technical field [0001] The invention belongs to the field of ceramic matrix composite materials, in particular to a Cf / MC-SiC composite material and a preparation method thereof. Background technique [0002] The thermal protection system of hypersonic vehicle nose cone, wing leading edge, rocket engine combustion chamber and other components is facing increasingly harsh working environment, which urgently requires the development and application of new ultra-high temperature resistant materials. Existing high-temperature-resistant materials such as refractory metals, graphite materials, C / C, and Cf / SiC composite materials can no longer meet the application requirements, so new material systems with ultra-high temperature resistance, ablation resistance, and oxidation resistance have been developed for new spacecraft development is of great significance. Ultra-high temperature ceramics have many excellent properties such as high melting point, good thermal stability, high t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83C04B35/65C04B35/565C04B38/02
CPCC04B35/565C04B35/65C04B35/83C04B38/02C04B2235/3839C04B2235/77C04B2235/96C04B2235/9607
Inventor 严春雷刘荣军曹英斌张长瑞王衍飞龙宪海李斌王思青
Owner NAT UNIV OF DEFENSE TECH
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