High temperature resistant ceramic matrix composite material and preparation method thereof

A technology of ultra-high temperature ceramics and composite materials, which is applied in the field of ultra-high temperature resistant ceramic matrix composite materials and its preparation technology, can solve the problems of difficult forming of large and complex components, poor reliability, and poor thermal shock resistance of materials, and achieve excellent thermal resistance. seismic performance, high reliability, high fracture toughness effect

Inactive Publication Date: 2008-07-23
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Commonly used ultra-high temperature resistant ceramics mainly include ZrB 2 +SiC, ZrB 2 +SiC+C, HfB 2 +SiC, etc. These materials have excellent ultra-high temperature resistance and

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0018] Example 1

[0019] A 2D C / ZrB 2 -SiC ultra-high temperature resistant ceramic matrix composite material, the composite material uses two-dimensional carbon fiber cloth as the reinforcing phase, and uses high melting point boride (ZrB 2 ) The ceramic powder is the filler, the silicon carbide is the matrix, and the volume fraction of the reinforcing phase carbon fiber is 25.45%, and the filler is ZrB 2 The volume fraction of the powder is 20.33%, the volume fraction of the SiC matrix is ​​35%, and the porosity is 19.22%.

[0020] The above 2D C / ZrB 2 -SiC ultra-high temperature resistant ceramic matrix composite material is prepared through the following steps:

[0021] (1) Prepare a mixed solution of PCS, divinylbenzene, and xylene in a mass ratio of 1:0.3:0.5, and then combine the mixed solution with ZrB 2 The powder is mixed at a volume ratio of 1:3, and then ball milled for 8 hours to form a slurry;

[0022] (2) Cut the 3K carbon fiber cloth produced by Jilin Carbon Facto...

Example Embodiment

[0027] Example 2

[0028] A 2D C / TaC-SiC ultra-high temperature resistant ceramic matrix composite material. The composite material uses two-dimensional carbon fiber cloth as a reinforcing phase, a high melting point carbide (TaC) ceramic powder as a filler, and silicon carbide as a matrix. The volume fraction of reinforcing phase carbon fiber is 20.5%, the volume fraction of filler TaC powder is 40.0%, the volume fraction of SiC matrix is ​​34.3%, and the porosity is 5.2%.

[0029] The above 2D C / TaC-SiC ultra-high temperature resistant ceramic matrix composite material is prepared through the following steps:

[0030] (1) Prepare a mixed solution of PCS and divinylbenzene at a mass ratio of 1:1, then mix the mixed solution with TaC powder at a volume ratio of 1:4, and form a slurry after ball milling for 8 hours;

[0031] (2) to (5) are the same as steps (2) to (5) of Example 1.

[0032] The density of the final 2D C / TaC-SiC ultra-high temperature resistant ceramic matrix compos...

Example Embodiment

[0033] Example 3

[0034] A 2D C / ZrB 2 -C Ultra-high temperature resistant ceramic matrix composite material, the composite material uses two-dimensional carbon fiber cloth as the reinforcing phase, with high melting point boride (ZrB 2 ) The ceramic powder is the filler, the carbon is the matrix, the volume fraction of the reinforcing phase carbon fiber is 44.8%, and the filler is ZrB2 The volume fraction of powder is 5.6%, the volume fraction of C matrix is ​​35%, and the porosity is 14.6%.

[0035] The above 2D C / ZrB 2 -C ultra-high temperature resistant ceramic matrix composite material is prepared through the following steps:

[0036] (1) Prepare a mixed solution of phenolic resin and acetone in a ratio of 1:1, and then combine the mixed solution with ZrB 2 The powder is mixed at a volume ratio of 1:1, and a slurry is formed after 8 hours of ball milling;

[0037] (2) and (3) are the same as steps (2) and (3) of embodiment 1;

[0038] (4) Put the above-mentioned lysed sample ...

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Abstract

The invention relates to an ultra-high temperature resistant ceramic-based composite and a preparation method, which adopts carbon or boron nitride fabric cloth as reinforcing phases, ceramic powders of high melting point or high-temperature resistant metal powders as the stuffing, and carbon/silicon carbide as the base. Through the blending and ball milling of the adhesives and the powder stuffing, the sizing agent thus acquired is coated on the reinforcing phase fabric cloth, and then overlapping, molding, cross-bonding, high-temperature pyrolysis, and repeated densification are carried out in preparing the composite. The ultra-high temperature resistant ceramic composite has the advantages of excellent thermal shock resistance, low density, and low ablating rate under ultra-high temperature.

Description

technical field [0001] The invention relates to a ceramic-based composite material and a preparation process thereof, in particular to an ultra-high temperature resistant ceramic-based composite material and a preparation process thereof. Background technique [0002] With the improvement of the flight speed of the aircraft and the requirements of high reliability and reusability, higher and higher requirements are put forward for the performance of materials. For example, when the aerospace vehicle re-enters the atmosphere, the speed is as high as Mach 30, forming a strong shock wave, and the air Being strongly compressed, the pressure and temperature rise sharply, and the nose cone and leading edge of the wing of the aircraft must withstand the severe heat of instantaneous ultra-high temperature (2000-3000 ℃) and large heat flow (tens of megawatts to hundreds of megawatts). environment. Another example is the hot-end parts of solid rocket motors (such as throat liners), w...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/52C04B35/565C04B35/622
Inventor 张长瑞胡海峰陈朝辉王其坤张玉娣王军赵丹
Owner NAT UNIV OF DEFENSE TECH
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