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High density ceramic matrix composite material, preparation method and application thereof

A composite material and ceramic-based technology, which is applied in the field of preparation of ceramic-based composite materials, can solve the problems of low self-diffusion coefficient, difficult density and toughness of ceramic materials, and difficulty in preparing dense monomers, and achieves high density and high density. The effect of toughness and high strength

Active Publication Date: 2014-02-05
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to its low self-diffusion coefficient and the presence of covalent bonds, denser ZrB can be prepared at lower temperature 2 Single is more difficult
Therefore, it was determined that ZrB 2 It is difficult to obtain higher density and better toughness for base ceramic materials
Especially when the hypersonic vehicle is in an environment with a large aerodynamic load, the ZrB 2 Such defects in base ceramic materials can spell fatal disaster for aircraft

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] Example 1, preparation and performance test of zirconium diboride-zirconium disilicide-tungsten carbide matrix composite material.

[0034] 1. Preparation

[0035] (1) The particle size of the raw material zirconium diboride, zirconium disilicide and tungsten carbide powder is 1-2 microns, the purity of the three powders is higher than 99.9%, and the mass parts are 75% of zirconium boride and 15% of zirconium disilicide %, tungsten carbide 10%;

[0036] (2) Mixing: Put the raw materials into a planetary ball mill whose grinding ball material is tungsten carbide, and mix them, and use absolute ethanol as a dispersion medium during ball milling. Raw materials, balls and dispersing medium are ball milled in a mass ratio of 1:10:1. During the powder milling process, the inner chamber of the milling tank is protected by filling inert gas to prevent the oxidation of the powder raw materials during the ball milling process. The rotational speed of the ball mill was 200 rpm. ...

Embodiment 2

[0045] Example 2, preparation and performance test of zirconium diboride-zirconium disilicide-tungsten carbide matrix composite material.

[0046] The average particle size of the raw materials zirconium diboride, zirconium disilicide and tungsten carbide powder is 1-2 microns, the purity of the three powders is higher than 99.9%, and the mass parts are 75% of zirconium boride, 15% of zirconium disilicide, 10% tungsten carbide; the mixing process and parameters are the same as in Example 1; and the sintering environment is in a high vacuum environment, the sintering temperature is 1450 ° C, the sintering pressure is 30 MPa, and the sintering time is 280 minutes.

[0047] The test process of the prepared material is the same as in Example 1. The test result is: the fracture toughness is 6.2MPa m 1 / 2 , the bending strength is 584MPa, and the relative density is 98.91%.

Embodiment 3

[0048] Example 3, preparation and performance test of zirconium diboride-zirconium disilicide-tungsten carbide matrix composite material.

[0049] The particle size of the raw material zirconium diboride, zirconium disilicide and tungsten carbide powder is 3-4 microns, the purity of the three powders is higher than 99.9%, and the mass parts are 80% zirconium boride, 10% zirconium disilicide, 10% tungsten; the mixing process and parameters are the same as in Example 1; and the sintering environment is in a high vacuum environment, the sintering temperature is 1550°C, the sintering pressure is 45MPa, and the sintering time is 300 minutes.

[0050] The test process of the prepared material is the same as in Example 1. The test result is: the fracture toughness is 6.5MPa m 1 / 2 , the bending strength is 514MPa, and the relative density is 98.24%.

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Abstract

The invention discloses a high density ceramic matrix composite material, a preparation method and application thereof. A zirconium diboride-zirconium disilicide-tungsten carbide ceramic matrix composite material is prepared from zirconium diboride powder, zirconium disilicide and tungsten carbide with purity of greater than 98% by a two-step hot pressing sintering process. Specifically, the mass fraction of zirconium diboride powder is 75-90%, and the adding of high content zirconium diboride into the ceramic matrix composite material is in favor of improving the physical and chemical performance of the composite material. The mass fraction of zirconium disilicide is 10-15%, and the adding of the zirconium disilicide with the mass fraction into the ceramic matrix composite material can significantly lower the sintering temperature of the material. The mass fraction of tungsten carbide is 0-10%, the added tungsten carbide can promote the anisotropic growth of crystal grains in the material. The grain size of the three original powder is 1-5 microns, and the grain size in the range is conducive to uniform mixing of each phase. The material provided by the invention can be used as a surface heat insulation layer of hypersonic flight vehicles, and has the characteristics of high density and high mechanical properties.

Description

technical field [0001] The invention belongs to the technical field of ceramic matrix composite materials, and relates to a preparation method of a ceramic matrix composite material with high density and excellent mechanical properties. Background technique [0002] With the development of hypersonic aircraft, its flight speed has exceeded 5Ma, causing the aircraft to be subjected to a huge aerodynamic load when it re-enters the atmosphere, prompting the surface of the aircraft to heat up rapidly in a short period of time. Therefore, an efficient heat insulation / heat protection system (thermal protection system) is required on the surface of the aircraft to ensure that the aircraft is within a safe temperature range, especially key parts (such as nose cones, wing edges, etc.) need stable physical and chemical properties in high temperature environments Structural materials. Typical service environments for thermal protection systems are: extreme harsh environments such as h...

Claims

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Application Information

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IPC IPC(8): C04B35/58C04B35/622
Inventor 沙建军韦志强李建代吉祥
Owner DALIAN UNIV OF TECH
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