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Novel ultrahigh-temperature ceramic integrally-modified anti-ablation carbon/carbon composite material and preparation method thereof

A technology of carbon composite materials and ultra-high temperature ceramics, which is applied in the field of new ultra-high temperature ceramic integrated modified anti-ablation carbon/carbon composite materials and its preparation, to achieve good anti-oxidation properties, improve thermal shock resistance, and relieve thermal stress Effect

Active Publication Date: 2017-08-08
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Among them, the infiltration reaction method has many advantages such as rapid preparation, easy composition adjustment, near-net shape and low cost; the embedding method has the advantages of low cost, fast and easy preparation of large-scale coatings; Integrative modification of carbon / carbon composites by combining infiltration and embedding methods

Method used

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  • Novel ultrahigh-temperature ceramic integrally-modified anti-ablation carbon/carbon composite material and preparation method thereof
  • Novel ultrahigh-temperature ceramic integrally-modified anti-ablation carbon/carbon composite material and preparation method thereof
  • Novel ultrahigh-temperature ceramic integrally-modified anti-ablation carbon/carbon composite material and preparation method thereof

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Embodiment 1

[0040] It is prepared by mixing zirconium powder and titanium powder with a purity greater than 99.9% at an atomic ratio of 80:20, and then ball milling on a high-energy planetary ball mill. The ball milling speed is 400r / min, the ball milling time is 10h, the ball-to-material ratio is 5, and the ball milling medium is absolute ethanol. The ball-milled powder was dried in a vacuum oven at 80° C. for 8 hours before being used in subsequent steps.

[0041] Set the density to 0.42g.cm -3 The carbon fiber needle-punched integral felt is subjected to high-temperature heat treatment to remove the organic glue on the surface of the fiber and release the stress. The treatment temperature is 2200°C, and the holding time is 1h.

[0042] The heat-treated felt is placed in a chemical vapor deposition furnace to deposit pyrolytic carbon, and the carbon fiber felt is densified to prepare a porous carbon / carbon composite material. The densified porous carbon / carbon composite has a density...

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Abstract

The invention discloses a novel ultrahigh-temperature ceramic (Zr0.8Ti0.2C0.74B0.26) integrally-modified anti-ablation carbon / carbon composite material and a preparation method thereof. The preparation method comprises the following steps: (1) performing high-temperature thermal treatment on a carbon fiber preform, and depositing pyrolytic carbon in a chemical gas phase permeation furnace to prepare a porous carbon / carbon composite material; (2) placing the carbon / carbon composite material on which the pyrolytic carbon is deposited on zirconium-titanium mixed powder, and preparing a zirconium-titanium carbide modified carbon / carbon composite material in a non-stoichiometric ratio through a high-temperature infiltration reaction method; (3) placing the composite material in mixed powder of C, B4C, SiC, Si and a penetration enhancer, and forming an integral ultrahigh-temperature ceramic modified carbon / carbon composite material by adopting an embedding method. The method is simple, is convenient to operate, can be used for preparing large-sized components, and is suitable for integrally modifying substrates and coatings of anti-ablation carbon / carbon composite materials in heat-resistant components of hypersonic aircrafts.

Description

technical field [0001] The invention relates to a novel ultra-high temperature ceramic integrated modified anti-ablation carbon / carbon composite material and a preparation method thereof. Background technique [0002] Carbon / carbon composite materials have low density, high specific strength, high specific modulus, and excellent high-temperature mechanical properties, and are important high-temperature structural materials for aviation / aerospace vehicles. However, traditional C / C composites have the problem of easy oxidation and cannot be used in oxidizing high-temperature environments. Zr, Ta, Hf and other transition metal carbides and boride ultra-high temperature ceramics have high melting point and good oxidation resistance and ablation resistance, but their thermal shock resistance is poor. Therefore, in recent years, material workers from various countries have been committed to introducing ultra-high temperature ceramics into carbon / carbon composite materials to prep...

Claims

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Application Information

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IPC IPC(8): C04B35/83C04B41/87C04B41/52
CPCC04B35/83C04B41/009C04B41/52C04B41/87C04B2235/422C04B2235/5248C04B41/5057C04B41/4556C04B41/5053C04B41/4558C04B35/52C04B35/5611C04B35/5622C04B35/80C04B2235/3232C04B2235/3821C04B2235/3826C04B2235/3839C04B2235/3843C04B2235/44C04B2235/608C04B2235/614C04B2235/616C04B2235/79C04B2235/80C04B41/4523C04B41/507C04B41/4529
Inventor 曾毅熊翔王滴泥孙威陈招科王雅雷
Owner CENT SOUTH UNIV
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