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

A composite material, c-sic-cu technology, applied in metal material coating process, gaseous chemical plating, coating and other directions, can solve the mechanical properties, thermal conductivity, ablation resistance and friction properties of composite materials. problems, to achieve the effect of improving thermal conductivity and mechanical properties, bonding tightly, and reducing the melting point of the alloy

Inactive Publication Date: 2021-03-30
中京吉泰(北京)科技有限责任公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0011] The invention provides a C / C-SiC-Cu composite material to solve the technical problems that the mechanical properties, thermal conductivity, ablation resistance and friction performance of the composite material in the prior art are not good enough

Method used

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

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Embodiment 1

[0063] This embodiment provides a C / C-SiC-Cu composite material and a preparation method thereof.

[0064] The C / C-SiC-Cu composite material of the present invention is mainly made of carbon fiber prefabricated body, matrix carbon, matrix silicon carbide, and copper-zirconium alloy; matrix carbon, matrix silicon carbide are deposited sequentially on the carbon fiber prefabricated body, and copper is infiltrated Zirconium alloy; the carbon fiber preform is a porous material.

[0065] The matrix carbon, the matrix silicon carbide, and the copper-zirconium alloy are sequentially attached to the pore walls of the carbon fiber prefabricated body.

[0066] The copper-zirconium alloy is infiltrated into the pores of the carbon fiber preform C / C-SiC porous body by vacuum infiltration. The zirconium element in the copper-zirconium alloy chemically reacts with the matrix silicon carbide deposited on the pore wall to form zirconium carbide and zirconium-silicon compound. The mixture, th...

Embodiment 2

[0087] This embodiment provides a C / C-SiC-Cu composite material and a preparation method thereof.

[0088] The C / C-SiC-Cu composite material of the present invention is mainly made of carbon fiber prefabricated body, matrix carbon, matrix silicon carbide, and copper-zirconium alloy; matrix carbon, matrix silicon carbide are deposited sequentially on the carbon fiber prefabricated body, and copper is infiltrated Zirconium alloy; the carbon fiber preform is a porous material.

[0089] The matrix carbon, the matrix silicon carbide, and the copper-zirconium alloy are sequentially attached to the pore walls of the carbon fiber prefabricated body.

[0090] The copper-zirconium alloy is infiltrated into the pores of the C / C-SiC porous body by vacuum infiltration. The zirconium element in the copper-zirconium alloy chemically reacts with the matrix silicon carbide deposited on the pore wall to form a mixture of zirconium carbide and zirconium-silicon compound. The copper-zirconium al...

Embodiment 3

[0108] This embodiment provides a C / C-SiC-Cu composite material and a preparation method thereof.

[0109] The C / C-SiC-Cu composite material of the present invention is mainly made of carbon fiber prefabricated body, matrix carbon, matrix silicon carbide, and copper-zirconium alloy; matrix carbon, matrix silicon carbide are deposited sequentially on the carbon fiber prefabricated body, and copper is infiltrated Zirconium alloy; the carbon fiber preform is a porous material.

[0110] The matrix carbon, the matrix silicon carbide, and the copper-zirconium alloy are sequentially attached to the pore walls of the carbon fiber prefabricated body.

[0111] The copper-zirconium alloy is infiltrated into the pores of the C / C-SiC porous body by vacuum infiltration. The zirconium element in the copper-zirconium alloy chemically reacts with the matrix silicon carbide deposited on the pore wall to form a mixture of zirconium carbide and zirconium-silicon compound. The copper-zirconium al...

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Abstract

The invention discloses a C / C-SiC-Cu composite material and a preparation method thereof. The C / C-SiC-Cu composite material is mainly prepared from a carbon fiber preform, matrix carbon, matrix silicon carbide and a copper-zirconium alloy, matrix carbon and matrix silicon carbide are sequentially deposited on the carbon fiber prefabricated body, and copper-zirconium alloy is infiltrated; and the carbon fiber prefabricated body is made of a porous material. The invention further discloses a preparation method of the C / C-SiC-Cu composite material. Vapor deposition silicon carbide on the surfaceof a carbon base material is combined with infiltration of a copper-zirconium alloy infiltration agent to form a spontaneous infiltration system, a high-pressure environment is not needed, the densityof the material can still be ensured, and the material has good mechanical, heat-conducting, ablation-resisting and friction-resisting properties.

Description

technical field [0001] The invention relates to a composite material and a preparation method thereof, in particular to a C / C-SiC-Cu composite material and a preparation method thereof. Background technique [0002] Hypersonic aircraft has the characteristics of fast response and strong defense penetration capabilities, and has great military value and potential. It is an extremely important and indispensable part of the future aviation field. At present, both at home and abroad attach great importance to this and have done a lot of research. Because the aircraft flies at hypersonic speed, it will inevitably generate a lot of heat, and the service temperature is extremely high. Therefore, the key components in the aircraft need to have excellent thermal protection performance and mechanical properties at high temperatures to ensure that the aircraft can fly at hypersonic speed for a long time. [0003] Although the service temperature of C / C composites is very high, which ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83C04B35/52C04B35/622C23C16/26C23C16/32B22D23/04
CPCB22D23/04C04B35/52C04B35/622C04B35/83C04B2235/3826C04B2235/404C04B2235/407C04B2235/5248C04B2235/77C04B2235/96C04B2235/9607C04B2235/9615C23C16/26C23C16/325
Inventor 龙宪海周峰何家琪汪莉匡湘铭王成华黄日升杨敏
Owner 中京吉泰(北京)科技有限责任公司
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