C / C-SiC composite material and preparation method and application thereof

A composite material and mixing technology, applied in mechanical equipment, friction linings, gear transmission mechanisms, etc., can solve the problem of large-scale industrialization and meet high-end industrial applications, low material density and mechanical properties, long production cycle, etc. problem, to achieve the effect of superior performance, excellent mechanical properties, and consistent overall performance

Active Publication Date: 2017-10-20
HUNAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] For C/C-SiC composite material preparation processes such as chemical vapor infiltration (CVI) and precursor conversion (PIP) and chemical vapor infiltration-melting silicon infiltration (CVI-RMI), there are long production cycles and high manufacturing costs. As well as the problem of low material density and mechanical properties in the warm-compression-in-situ reaction method (WCISR) an...

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  • C / C-SiC composite material and preparation method and application thereof
  • C / C-SiC composite material and preparation method and application thereof
  • C / C-SiC composite material and preparation method and application thereof

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Embodiment 1

[0046] This embodiment provides a method for preparing a C / C-SiC composite material. The C / C-SiC composite material is a multilayer symmetrical gradient structure, such as figure 1 The multi-layer symmetrical gradient structure shown from the inner layer to the outer layer is the middle layer, the upper and lower symmetrical 6mm chopped carbon fiber reinforced silicon carbide matrix layer 2 and the upper and lower symmetrical 3mm chopped carbon fiber reinforced silicon carbide matrix layer 1, and the middle layer is 90° Plain carbon fiber The toughening layer 4 and the 45° plain carbon fiber toughening layer 3 are interlaced to form a reinforced and toughened interlayer, the carbon fiber content of the 3mm chopped carbon fiber reinforced silicon carbide matrix layer 1 is 20vol%, and the 6mm chopped carbon fiber reinforced silicon carbide matrix layer 2 The carbon fiber content is 50vol%;

[0047] Include the following steps:

[0048] S1. Preparation of carbon fiber reinforced...

Embodiment 2

[0058] This embodiment provides a method for preparing a C / C-SiC composite material. The C / C-SiC composite material is a multilayer symmetrical gradient structure, such as figure 1 The multi-layer symmetrical gradient structure shown from the inner layer to the outer layer is the middle layer, the upper and lower symmetrical 10mm chopped carbon fiber reinforced silicon carbide matrix layer 2 and the upper and lower symmetrical 6mm chopped carbon fiber reinforced silicon carbide matrix layer 1, and the middle layer is 90° Plain carbon fiber The toughening layer 4 and the 45° plain carbon fiber toughening layer 3 are interlaced to form a reinforced and toughened interlayer, the carbon fiber content of the 6mm chopped carbon fiber reinforced silicon carbide matrix layer 1 is 30vol%, and the 12mm chopped carbon fiber reinforced silicon carbide matrix layer 2 Carbon fiber content is 60vol%;

[0059] Include the following steps:

[0060] S1. Preparation of carbon fiber reinforced p...

Embodiment 3

[0070] This embodiment provides a method for preparing a C / C-SiC composite material. The C / C-SiC composite material is a multilayer symmetrical gradient structure, such as figure 1 The multi-layer symmetrical gradient structure shown from the inner layer to the outer layer is the middle layer, the upper and lower symmetrical 8mm chopped carbon fiber reinforced silicon carbide matrix layer 2 and the upper and lower symmetrical 4mm chopped carbon fiber reinforced silicon carbide matrix layer 1, and the middle layer is 90° Plain carbon fiber The toughening layer 4 and the 45° plain carbon fiber toughening layer 3 are interlaced to form a reinforced and toughened interlayer. The carbon fiber content of the 4mm chopped carbon fiber reinforced silicon carbide matrix layer 1 is 30vol%, and the 15mm chopped carbon fiber reinforced silicon carbide matrix layer 2. Carbon fiber content is 60vol%;

[0071] Include the following steps:

[0072]S1. Preparation of carbon fiber reinforced pl...

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Abstract

The present invention discloses a C / C-SiC composite material and a preparation method and application thereof. The C / C-SiC composite is a multilayer symmetrical gradient structure, the symmetrical multilayer gradient structure comprises from the inner layer to the outer layer in turn a middle layer, a longitudinally-symmetrical second layer short-cut carbon fiber reinforced silicon carbide layer and a longitudinally-symmetrical first layer short-cut carbon fiber reinforced silicon carbide layer, the carbon fiber content of the first layer short-cut carbon fiber reinforced silicon carbide layer is lower than that of the second layer short-cut carbon fiber reinforced silicon carbide layer, and the middle layer is a 90 DEG and 45 DEG plain carbon fiber cloth interlaced superposed reinforced toughened interlayer. The C / C-SiC composite is prepared from short-cut carbon fiber, plain carbon fiber cloth, phenolic resin and industrial silica fume as raw materials by compression molding, curing, carbonization and infiltration. Products prepared by the C / C-SiC composite material have high density, excellent mechanical property, oxidation resistance, friction and wear resistance and fatigue resistance, and are suitable for the fields of high end industries such as high speed and high energy transportation vehicles.

Description

technical field [0001] The present invention relates to the technical field of C / C-SiC composite materials, and more specifically, relates to a C / C-SiC composite material and its preparation method and application. Background technique [0002] C / C-SiC composite material has good oxidation resistance, corrosion resistance, excellent mechanical and thermophysical properties, and is a high-temperature structural functional material. Once it came out, it attracted great attention from scholars in the field of aerospace materials. Applied to panels, winglets, elevons and fuselage hatches of returnable spacecraft, thermal protection systems of space shuttles, space mirrors and other components and products. The material also has a density less than 2g / cm 3 , good wear resistance, high thermal conductivity, good oxidation resistance, high and stable friction performance, corrosion resistance, not affected by weather changes, still has a high friction coefficient and low wear rate...

Claims

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Application Information

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IPC IPC(8): C04B35/524C04B35/565C04B35/80C04B35/622F16D69/02
CPCC04B35/524C04B35/573C04B35/622C04B35/806C04B2235/428C04B2235/5248C04B2235/616C04B2235/77C04B2235/96F16D69/023F16D2200/0047
Inventor 周伟
Owner HUNAN UNIV OF TECH
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