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Cf/C-SiC-ZrC composite material and preparation method thereof

A composite material, c-sic-zrc technology, applied in the field of carbon fiber toughened ceramic matrix composite materials, can solve the problems of brittle fracture, limited application, lack of plastic deformation of ceramic materials, etc., to improve fracture toughness and strength, and improve fracture toughness Effect

Inactive Publication Date: 2019-09-27
UNIV OF JINAN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the formation of its own chemical bonds, ceramic materials lack the ability of plastic deformation and have the characteristics of brittle fracture, which limits their application in aerospace and other fields.

Method used

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  • Cf/C-SiC-ZrC composite material and preparation method thereof
  • Cf/C-SiC-ZrC composite material and preparation method thereof
  • Cf/C-SiC-ZrC composite material and preparation method thereof

Examples

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Effect test

Embodiment 1

[0035] Using T700 12K carbon fiber from Toray Corporation of Japan as the raw material, the volume fraction is 40% and the initial density is 0.7 g / cm through three-dimensional weaving 3 The prefabricated carbon fiber woven prefabricated body is degummed at 900 ℃, and the prefabricated body after the degummed treatment is prepared in a chemical vapor deposition furnace for pyrolytic carbon PyC interface layer. The gas source is propane, and the flow rate is controlled at 2 L / min, the dilution gas is Ar, the flow rate is controlled at 4 L / min, the deposition temperature is 1000 °C, the deposition time is 24 h, and the density is 0.9 g / cm 3 carbon fiber preforms.

[0036] Using xylene as a solvent, polycarbosilane and polycarbozircones are mixed according to a mass ratio of 1:3, stirred until polycarbosilanes and polycarbozircones are completely dissolved in xylene solvent, and then the density is 0.9 g / cm 3 The carbon fiber prefabricated body was immersed in the mixed solutio...

Embodiment 2

[0039]Using T700 12K carbon fiber from Toray Corporation of Japan as the raw material, the volume fraction is 50% and the initial density is 1.1 g / cm through three-dimensional weaving. 3 The prefabricated carbon fiber braided prefabricated body was degummed at 950 °C, and the PyC interface layer was prepared in a chemical vapor deposition furnace after the degummed prefabricated body. The gas source was propane, and the flow rate was controlled at 3 L / min, the dilution gas is Ar, the flow rate is controlled at 3 L / min, the deposition temperature is 950 °C, the deposition time is 36 h, and the density is 1.4 g / cm 3 carbon fiber preforms.

[0040] Using xylene as a solvent, polycarbosilane and polycarbozircones were prepared in a mass ratio of 1:1, mixed and then magnetically stirred until polycarbosilanes and polycarbozircones were completely dissolved in xylene solvent, Then set the density to 1.4g / cm 3 The carbon fiber prefabricated body was immersed in the mixed solution,...

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Abstract

The invention relates to a Cf / C-SiC-ZrC composite material and a preparation method thereof, and belongs to the field of carbon fiber toughened ceramic matrix composite materials. The Cf / C-SiC-ZrC composite material with high fracture toughness property is prepared by using a process combining chemical vapor deposition and a precursor infiltration and pyrolysis method. The specific preparation method comprises the following steps: first, performing rubber discharge and pyrolysis carbon PyC interface layer deposition on a carbon fiber preform; then immersing in a mixed solution of PCS and PZC; performing impregnation, curing and cracking treatment; circulating the impregnation-curing-cracking process to obtain the Cf / C-SiC-ZrC composite material. The Cf / C-SiC-ZrC composite material prepared by the method of the invention can effectively reduce the physical and chemical damage to the carbon fiber during the cracking process under the protection of a PyC interface layer, and cracks transmitted from a ceramic matrix to the carbon fiber is deflected on the interface layer. In addition, the PyC interface layer is beneficial to the weakening of interface bonding force between the carbon fiber and the ceramic matrix; when the Cf / C-SiC-ZrC composite material breaks, energy is dissipated through the pull-out of the carbon fiber, so that the fracture toughness property of the Cf / C-SiC-ZrC composite material is improved.

Description

technical field [0001] The invention belongs to the field of carbon fiber toughened ceramic matrix composite materials, and specifically relates to the preparation of C f / C-SiC-ZrC composite method. Background technique [0002] With the continuous development of aerospace technology, hypersonic vehicles have become the main development direction of the aerospace field and weapon systems, and they are also the strategic technological commanding heights that major military powers are striving to seize. However, with the increase of flight speed, the environment in which the aircraft is in service is getting harsher, and the requirements for the selection of aircraft structural materials are more stringent. [0003] Among the various materials currently being studied, carbide ultra-high temperature ceramic materials, especially SiC and ZrC ceramic materials, are used in some demanding applications because of their excellent properties such as high strength, high hardness, we...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/56C04B35/571C04B35/83
CPCC04B35/5622C04B35/571C04B35/806C04B35/83C04B2235/3826C04B2235/3839C04B2235/422C04B2235/5248C04B2235/606C04B2235/656C04B2235/6567C04B2235/658C04B2235/77C04B2235/96
Inventor 刘福田苏纯兰周长灵徐鸿照姜凯杨芳红
Owner UNIV OF JINAN
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