Carbon fiber enhanced hafnium boride-tantalum boride-carbon ceramic-based composite material and preparation method thereof

A composite material and carbon fiber preform technology, applied in the field of ceramic matrix composite materials, can solve the problem that the ceramic matrix composite materials cannot be modified by tantalum boride and hafnium boride at the same time, and the refractory tantalum boride and hafnium boride composite materials are evenly distributed and other problems, to achieve the effect of easy industrialization, outstanding mechanical properties, and low preparation temperature

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

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Problems solved by technology

Although the chemical vapor deposition method can be used to deposit hafnium boride and tantalum boride composite coatings at present, it is difficult for the raw materials and methods in the prior art to ma...

Method used

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  • Carbon fiber enhanced hafnium boride-tantalum boride-carbon ceramic-based composite material and preparation method thereof
  • Carbon fiber enhanced hafnium boride-tantalum boride-carbon ceramic-based composite material and preparation method thereof

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preparation example Construction

[0025] In a first aspect, the present invention provides a method for preparing a carbon fiber reinforced hafnium boride-tantalum boride-carbon ceramic matrix composite material, the method comprising the following steps:

[0026] (1) impregnating the carbon fiber preform with a hafnium-tantalum precursor solution containing a hafnium-tantalum precursor copolymer, a boron source precursor, a carbon source precursor and an organic solvent, and then curing and cracking the impregnated carbon fiber preform in sequence steps; and

[0027] (2) Step (1) is repeated several times to obtain a carbon fiber reinforced hafnium boride-tantalum boride-carbon ceramic matrix composite material.

[0028] In the present invention, the hafnium-tantalum precursor solution is, for example, obtained by dissolving a hafnium-tantalum precursor copolymer, a boron source precursor, and a carbon source precursor in an organic solvent, wherein the hafnium-tantalum precursor copolymer is used to provide ...

Embodiment 1

[0058] a C f / HfB 2 -TaB 2 -C composite material preparation method, using the impregnation cracking method of hafnium-tantalum precursor to prepare dense C f / HfB 2 -TaB 2 -C composite material, wherein the viscosity of the hafnium-tantalum precursor solution is 230mpa·s, and the solid content of the solution is 60%. The specific steps are:

[0059] ①The needle-punched carbon fiber braid was treated at a high temperature of 1700°C for 3 hours, and then deposited in a vapor deposition furnace for 60 hours, 120 hours, and 100 hours respectively to obtain a density of 1.03g / cm 3 carbon fiber preforms.

[0060] ②Impregnate the carbon fiber prefabricated body obtained in step ① under a vacuum of 0.05MPa for 1h (first pressure stage impregnation), then impregnate under 2MPa pressure for 1.5h (second pressure stage impregnation), and finally pressurize to 10MPa ( curing pressure), and heat up to 70°C for 1.5h (first temperature stage curing), 180°C for 1.5h (second temperature...

Embodiment 2

[0065] a C f / HfB 2 -TaB 2 -C composite material preparation method, using the impregnation cracking method of hafnium-tantalum precursor to prepare dense C f / HfB 2 -TaB 2 -C composite material, wherein the viscosity of the hafnium-tantalum precursor solution is 230mpa·s, and the solid content of the solution is 60%. The specific steps are:

[0066] ①The stitched carbon fiber braid 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 120 hours respectively, and the obtained density reached 1.18g / cm 3 carbon fiber preforms.

[0067] ②Impregnate the carbon fiber prefabricated body obtained in step ① under a vacuum of 0.05MPa for 1h, then under a pressure of 3MPa for 2h, and finally pressurize to 15MPa (curing pressure), and raise the temperature to 70°C for 2h, 180°C Keeping the temperature for 2 hours under 300° C. for 2 hours makes the precursor of hafnium and tantalum fully cross-linked an...

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Abstract

The invention relates to a carbon fiber enhanced hafnium boride-tantalum boride-carbon ceramic-based composite material and a preparation method thereof. The method comprises the following steps: (1)soaking carbon fiber prefabricated bodies into a tantalum hafnium precursor solution containing a tantalum hafnium precursor copolymer, a boron source precursor, a carbon source precursor and an organic solvent; then, sequentially curing and cracking the soaked carbon fiber prefabricated bodies; (2) repeating the steps (1) for many times to prepare the carbon fiber enhanced hafnium boride-tantalumboride-carbon ceramic-based composite material. The preparation method has the advantages that the process is simple; the addition of additives is not needed; the preparation temperature is low; thepreparation period is short; the industrial implementation is easy, and the like. The prepared carbon fiber enhanced hafnium boride-tantalum boride-carbon ceramic-based composite material has the advantages of high toughness, super-high-temperature resistance, excellent anti-oxidization performance, excellent ablation resistance performance and the like.

Description

technical field [0001] The invention belongs to the technical field of ceramic matrix composite materials, in particular to a carbon fiber reinforced hafnium boride-tantalum boride-carbon ceramic matrix composite material and a preparation method thereof. Background technique [0002] Continuous carbon fiber toughened silicon carbide ceramic matrix composite (C / SiC composite) is an ideal high-temperature structural material with a series of advantages such as high temperature resistance, low density, high strength, and thermal shock resistance. It has a wide range of applications in the aerospace field. application prospects. Because aerospace vehicles not only need to be used normally under the harsh conditions of high speed and ultra high temperature, but also need to have excellent performance of high reliability and long life, this requires aerospace materials to have more excellent and stable performance and corresponding preparation processes. [0003] Borides and car...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/58C04B35/52
CPCC04B35/521C04B35/58064C04B35/58078C04B35/80C04B2235/3813C04B2235/422C04B2235/5248C04B2235/656C04B2235/6567C04B2235/658C04B2235/77C04B2235/96C04B2235/9607C04B2235/9684
Inventor 金鑫刘伟于新民刘俊鹏左红军霍鹏飞裴雨辰
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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