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C/ZrC ceramic matrix composite and preparation method thereof

A composite material and ceramic-based technology, which is applied in the field of ceramic-based composite materials and their preparation, can solve problems such as high requirements, complex processes, and high material brittleness, and achieve the effects of simple equipment requirements, simplified preparation processes, and low preparation costs

Inactive Publication Date: 2010-05-19
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The current molding method of ZrC ultra-high temperature resistant ceramic materials is mainly to prepare ZrC body ceramics by hot pressing process. The biggest disadvantage of hot pressing process is that the obtained material is brittle and has poor thermal shock resistance. In addition, hot pressing process has high requirements for equipment. , complex process, high energy consumption

Method used

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  • C/ZrC ceramic matrix composite and preparation method thereof
  • C/ZrC ceramic matrix composite and preparation method thereof
  • C/ZrC ceramic matrix composite and preparation method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0018] A C / ZrC ceramic matrix composite material of the present invention, the composite material uses carbon fiber as a reinforcing and toughening phase (the carbon fiber preform adopts a three-dimensional woven structure), and uses ZrC as a matrix. The volume fraction of ZrC in the composite material is 41%, the volume fraction of carbon fiber is 50%, and the porosity is 9%.

[0019] The above-mentioned C / ZrC ceramic matrix composite material is prepared by the following steps:

[0020] 1. Preparation of carbon fiber preforms: Using continuous carbon fibers as raw materials, the carbon fiber preforms are prepared by three-dimensional four-way weaving, and the fiber volume fraction in the carbon fiber preforms is 50%;

[0021] 2. Preparation of C / C composite material: Based on the carbon fiber preform obtained in step 1 of this example, using phenolic resin as raw material, the C / C composite material is obtained by the resin liquid phase impregnation and cracking method. The...

Embodiment 2

[0026] A C / ZrC ceramic matrix composite material of the present invention, the composite material uses carbon fiber as a reinforcing and toughening phase (the carbon fiber preform adopts a needle-punched carbon fiber felt structure), and uses ZrC as a matrix. The volume of ZrC in the composite material The fraction is 63%, the volume fraction of carbon fiber is 30%, and the porosity is 7%.

[0027] The above-mentioned C / ZrC ceramic matrix composite material is prepared by the following steps:

[0028] 1. Preparation of carbon fiber preforms: carbon fiber preforms with felt structure are prepared by needle punching, and the fiber volume fraction in the carbon fiber preforms is 30%;

[0029] 2. Preparation of C / C composite material: Based on the carbon fiber preform obtained in step 1 of this example, chemical vapor deposition combined with resin liquid phase impregnation cracking method (first chemical vapor deposition process is used to make fiber in the carbon fiber preform)....

Embodiment 3

[0034] A C / ZrC ceramic matrix composite material of the present invention, the composite material uses ZrC as a matrix, a needle-punched carbon fiber felt as a reinforcing and toughening phase, the volume fraction of the matrix in the composite material is 52%, and the reinforcement increases. The volume fraction of tough phase in this composite is 40%, and the porosity is 8%.

[0035] The above-mentioned C / ZrC ceramic matrix composite material is prepared by the following steps:

[0036] 1. Preparation of carbon fiber preforms: The carbon fiber preforms are prepared by using the overall carbon felt as the raw material, and the carbon fiber preforms are prepared by the needle punching method, and the fiber volume fraction in the carbon fiber preforms is 40%;

[0037] 2. Preparation of C / C composite material: Based on the carbon fiber preform obtained in step 1 of this example, a C / C composite material is obtained by chemical vapor deposition combined with resin liquid phase im...

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Abstract

The invention discloses a C / ZrC ceramic matrix composite which uses ZrC as a matrix and uses carbon fiber as a reinforcing and toughening phase. The volume percent of the ZrC in the composite is 35%-65%, the volume percent of the carbon fiber in the composite is 25%-55%, and the porosity of the composite is 5%-15%. The preparation method of the composite comprises the steps of: preparing a C / C composite by using a carbon fiber preform as a matrix by using a chemical vapor deposition method or a resin liquid phase impregnating / cracking method or combining the chemical vapor deposition method and the resin liquid phase impregnating / cracking method; and then, obtaining the C / ZrC ceramic matrix composite by using metal Zr or the alloy of the Zr as a penetrating agent by the processes of metal infiltration reaction, high-temperature treatment after infiltration, and the like. The composite has ultra-temperature resistance, good fracture toughness, strong ablation resistance and good thermal shock resistance. The invention has simple preparation process, low cost, no corrosion to equipment, and no pollution to the environment.

Description

technical field [0001] The invention relates to a ceramic matrix composite material and a preparation method thereof, in particular to a ceramic matrix composite material using carbide as a matrix and a preparation method thereof. Background technique [0002] Extreme environments such as long-time hypersonic vehicle flight, atmospheric reentry, transatmospheric flight, and rocket propulsion systems place extremely stringent requirements on high-temperature thermal structural materials. The test of high temperature, but also to withstand the erosion of high-speed airflow and the corrosion of oxidizing gas. Existing C / SiC composite materials and C / C composite materials can no longer meet the use requirements of supersonic aircraft nose cones, wing leading edges, long-life engine combustion chambers and other components. The C / SiC composite material is mainly limited by its temperature resistance, and the best use temperature of the material is 1300℃~1650℃; although the servi...

Claims

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Application Information

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IPC IPC(8): C04B35/83C04B35/622
Inventor 王松祝玉林李伟张守明陈朝辉
Owner NAT UNIV OF DEFENSE TECH
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