Carbon fiber toughened ultra-high-temperature ceramic matrix composite capable of avoiding thermal mismatching and preparation method of carbon fiber toughened ultra-high-temperature ceramic matrix composite

A technology of ultra-high temperature ceramics and composite materials, which is applied in the field of carbon fiber toughened ultra-high temperature ceramic matrix composite materials and its preparation, can solve problems such as performance degradation of composite materials, and achieve improved thermal shock resistance, mechanical properties, and reliability. Effect

Active Publication Date: 2021-06-25
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to provide a carbon fiber toughened ultra-high temperature ceramic matrix composite material that avoids thermal mismatch and its preparation method. sex

Method used

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  • Carbon fiber toughened ultra-high-temperature ceramic matrix composite capable of avoiding thermal mismatching and preparation method of carbon fiber toughened ultra-high-temperature ceramic matrix composite
  • Carbon fiber toughened ultra-high-temperature ceramic matrix composite capable of avoiding thermal mismatching and preparation method of carbon fiber toughened ultra-high-temperature ceramic matrix composite
  • Carbon fiber toughened ultra-high-temperature ceramic matrix composite capable of avoiding thermal mismatching and preparation method of carbon fiber toughened ultra-high-temperature ceramic matrix composite

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] A carbon fiber toughened ultra-high temperature ceramic matrix composite material that avoids thermal mismatch. In the cross-sectional direction of the carbon fiber, there are n layers of gradient ceramic substrates with carbon fiber as the center and the thermal expansion coefficient gradually increases from the inside to the outside. The innermost ceramic substrate The raw materials include silicon carbide and zirconium disilicide; the raw materials of the outermost ceramic matrix include diboride ultra-high temperature ceramics and zirconium disilicide; the ceramic matrix raw materials of the middle layer include: diboride ultra-high temperature ceramics, silicon carbide, and zirconium disilicide; The diboride ultra-high temperature ceramic mentioned above is zirconium diboride; the volume of the carbon fiber toughened ultra-high temperature ceramic matrix composite is 100 parts, and the volume part of the carbon fiber is 40; The volume is 100 parts, the volume part o...

Embodiment 2

[0044] The difference between this example and Example 1 is that n=5; i=1, 2, 3, 4, 5; in step 4), the electrophoretic deposition time is 12 minutes. Such as figure 2 As shown, 5 layers of radially gradient ceramic coatings were coated on carbon fibers using electrophoretic deposition technology.

Embodiment 3

[0046] The difference between this example and Example 1 is that the diboride ultra-high temperature ceramic is hafnium diboride; based on 100 parts of carbon fiber toughened ultra-high temperature ceramic matrix composite material, the volume part of carbon fiber is 30; m=30 ; n=5; i=1, 2, 3, 4, 5; in step 4), the electrophoretic deposition time is 14 min.

[0047] To sum up, a carbon fiber toughened ultra-high temperature ceramic matrix composite material that avoids thermal mismatch of the present invention solves the problem of thermal mismatch between carbon fiber and matrix, improves the mechanical properties of the composite material, and avoids the composite material’s resistance to oxidation and anti-oxidation. The decline of ablation performance; the designed gradient ceramic matrix improves the fracture resistance and thermal shock resistance of the composite material; the pyrolytic carbon derived from the polymer reacts with zirconium disilicide to generate nano-sca...

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Abstract

The invention belongs to the field of ultrahigh-temperature ceramic-based composite materials, and particularly relates to a carbon fiber toughened ultrahigh-temperature ceramic-based composite material capable of avoiding thermal mismatching and a preparation method of the carbon fiber toughened ultrahigh-temperature ceramic-based composite material. In the section direction of the carbon fiber, n layers of gradient ceramic matrixes with thermal expansion coefficients gradually increasing from inside to outside with the carbon fiber as the center are arranged, and the ceramic matrixes are prepared from diboride ultra-high-temperature ceramic, silicon carbide and zirconium disilicide; the diboride superhigh temperature ceramic comprises zirconium diboride or hafnium diboride; the preparation method comprises the following steps: carrying out electrophoretic deposition on n layers of radial gradient ceramic coatings on carbon fibers, and then carrying out hot pressed sintering to obtain the composite material. The method has the advantages that the problem of thermal mismatching of the carbon fibers and the matrix is solved, the mechanical performance of the composite material is improved, and the oxidation resistance and ablation resistance of the composite material are prevented from being reduced; due to the designed gradient ceramic matrix, the fracture resistance and the thermal shock resistance of the composite material are improved; the matrix components are optimized, and the ultra-high temperature resistance of the composite material is improved.

Description

technical field [0001] The invention belongs to the field of ultra-high-temperature ceramic-based composite materials, and in particular relates to a carbon fiber-toughened ultra-high-temperature ceramic-based composite material for avoiding thermal mismatch and a preparation method thereof. Background technique [0002] Hypersonic missiles, transatmospheric vehicles, aerospace aircraft, etc. will suffer from a strong aerodynamic heating effect during flight, and the temperature of their sharp parts (such as nose cones and wing leading edges) will be as high as 2000 °C. This puts forward strict requirements on the materials used in service. Carbon fiber toughened carbon matrix composites have excellent fracture resistance, low density (~2g / cm 3 ), high strength, widely used in aerospace structural materials. However, in an aerobic ultra-high temperature environment (>1600°C), carbon fiber reinforced carbon matrix composites will be rapidly oxidized and ablated, resultin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/58C04B35/575C04B35/80C04B35/622C04B35/628C04B35/645
CPCC04B35/58078C04B35/58092C04B35/575C04B35/622C04B35/62873C04B35/62857C04B35/62863C04B35/62886C04B35/62894C04B35/645C04B2235/5248C04B2235/48C04B2235/656C04B2235/6567C04B2235/75C04B2235/96C04B2235/9607
Inventor 刘应军沙建军祖宇飞苏成代吉祥
Owner DALIAN UNIV OF TECH
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