Cf/HfC-TaC-C composite material and preparation method thereof

A composite material, hfc-tac-c technology, which is applied in the field of ceramic matrix composite materials, can solve the problems of unsatisfactory mechanical properties and inability to meet high-temperature use environments, and achieve easy industrial implementation, outstanding mechanical properties, and excellent ablation resistance. Effect

Inactive Publication Date: 2019-01-25
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The current ultra-high temperature ceramic matrix composites based on zirconium carbide-silicon carbide, zirconium boride-silicon carbide, hafnium carbide-silicon carbide, etc. are difficult to meet such a harsh high-temperature environment, and the matrix components of ceramic matrix composites need to be carried out. Improve
[0004] Tantalum carbide and hafnium carbide have high melting points and may be candidate materials for high-temperature structural parts of higher Mach number aircraft in the future. For example, patents CN200510012582.6 and CN200510012585.X have prepared tantalum carbide / carbon composites by hot pressing and self-sintering Material, the patent CN201410383873.5 utilizes chemical vapor deposition to prepare hafnium carbide modified carbon / carbon composite materials, but the mechanical properties of the composite materials containing tantalum carbide or hafnium carbide prepared in the above-mentioned patent are still not ideal enough to meet the This harsh high temperature environment

Method used

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  • Cf/HfC-TaC-C composite material and preparation method thereof

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] a C f / HfC-TaC-C composite material preparation method, using the impregnation pyrolysis method (PIP) of hafnium-tantalum precursor to prepare dense C f / HfC-TaC-C composite material, its specific steps are:

[0038] 1) The needle-punched carbon fiber preform was treated at a high temperature of 1700°C for 3 hours, and then deposited in a vapor deposition furnace for 100 hours, 150 hours, and 80 hours, so that the density of the preform reached 1.05g / cm 3 .

[0039] 2) Immerse the above-mentioned prefabricated body under a vacuum of 50KPa for 1 hour, then under a pressure of 3MPa for 1 hour, and finally pressurize to 10MPa, and raise the temperature to 100°C for 1 hour, and 200°C for 1 hour, Insulate at 350° C. for 1 hour to fully cross-link and solidify the hafnium-tantalum precursor.

[0040] 3) Put the solidified carbon fiber preform in a pyrolysis furnace, and pyrolyze at 1600° C. for 3 hours under an argon atmosphere.

[0041] 4) Repeat steps 2) and 3) 8 times, t...

Embodiment 2

[0047] a C f / HfC-TaC-C composite material preparation method, using the impregnation pyrolysis method (PIP) of hafnium-tantalum precursor to prepare dense C f / HfC-TaC-C composite material, its specific steps are:

[0048] 1) Treat the fine-woven and punctured carbon fiber preform at a high temperature of 1700°C for 3 hours, and then deposit it in a vapor deposition furnace for 80 hours, 100 hours, and 80 hours respectively, so that the density of the preform reaches 1.12g / cm 3 .

[0049] 2) Immerse the above-mentioned prefabricated body under a vacuum of 50KPa for 1 hour, then under a pressure of 3MPa for 1 hour, and finally pressurize to 10MPa, and raise the temperature to 100°C for 1 hour, and 200°C for 1 hour, Insulate at 350° C. for 1 hour to fully cross-link and solidify the hafnium-tantalum precursor.

[0050] 3) Put the solidified carbon fiber preform in a pyrolysis furnace, and pyrolyze at 1600° C. for 3 hours under an argon atmosphere.

[0051] 4) Repeat steps 2...

Embodiment 3

[0056] a C f / HfC-TaC-C composite material preparation method, using the impregnation pyrolysis method (PIP) of hafnium-tantalum precursor to prepare dense C f / HfC-TaC-C composite material, its specific steps are:

[0057] 1) The stitched carbon fiber preform was treated at a high temperature of 1700°C for 3 hours, and then deposited in a vapor deposition furnace for 100 hours, 120 hours, and 80 hours respectively, so that the density of the preform reached 1.18g / cm 3

[0058] 2) Immerse the above-mentioned prefabricated body under a vacuum of 50KPa for 1 hour, then under a pressure of 3MPa for 1 hour, and finally pressurize to 10MPa, and raise the temperature to 100°C for 1 hour, and 200°C for 1 hour, Insulate at 350° C. for 1 hour to fully cross-link and solidify the hafnium-tantalum precursor.

[0059] 3) Put the solidified carbon fiber preform in a pyrolysis furnace, and pyrolyze at 1600° C. for 3 hours under an argon atmosphere.

[0060] 4) Repeat steps 2) and 3) 8 t...

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Abstract

The invention provides a Cf/HfC-TaC-C composite material and a preparation method thereof, wherein a carbon fiber preform as a skeleton is immersed in a precursor solution containing a hafnium-tantalum precursor copolymer, and curing and cracking are performed to obtain the Cf/HfC-TaC-C composite material. According to the present invention, the process is simple, and the preparation period is short; and the prepared ultra-high temperature ceramic matrix composite material has advantages of excellent high-temperature resistance, excellent oxidation resistance and excellent ablation resistance,can be used as the high temperature thermal structure material of highly-hypersonic aircrafts and rocket propulsion systems, and has wide application prospect.

Description

technical field [0001] The invention relates to an ultra-high temperature ceramic matrix composite material and a preparation method thereof, in particular to a C f The invention relates to a HfC-TaC-C composite material and a preparation method thereof, belonging to the technical field of ceramic matrix composite materials. Background technique [0002] Ultra-high temperature ceramic matrix composites use continuous fibers as the skeleton, multi-component ceramics such as carbides or borides of refractory metals as the matrix, and an anti-oxidation coating is designed outside the matrix to prepare continuous fiber toughened Ultra-high temperature ceramic matrix composites, such as C / SiC-ZrC, C / SiC-HfB 2 、C f / Zr-Si-C composite materials, etc. It has low density, ultra-high temperature resistance, oxidation resistance and ablation resistance, and good high-temperature mechanical properties. It is the main candidate material for high-temperature structural parts of hyperso...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/622C04B35/52
CPCC04B35/806C04B35/52C04B35/622C04B2235/3839C04B2235/77C04B2235/9607C04B2235/96
Inventor 刘伟孙同臣刘俊鹏于新民王涛张安苏金鑫裴雨辰
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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