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Preparation method of Cf-ZrB2/ZrC/SiC composite material

A composite material, cf-zrb2 technology, applied in the field of preparation of Cf-ZrB2/ZrC/SiC composite materials, can solve the problems of poor thermal shock resistance, failure to meet the requirements of the century, large thermal expansion coefficient, etc., and achieve good high temperature resistance, cycle time Effect of short, good high temperature performance

Active Publication Date: 2013-10-02
SHANDONG RES & DESIGN ACADEMY OF IND CERAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, due to the active oxidation of the material at high temperature, the limit service temperature of this material is 1600-1650°C
Ultra-high temperature near-zero ablation ceramics mainly include ZrB 2 , HfB 2 , TaC, ZrC, SiC, etc. and their various composite materials, which have the characteristics of almost no ablation (ablation rate <0.001mm / s) in harsh environments such as high stress and strong oxidation, and at ultra-high temperatures above 2200°C Excellent properties, but this type of material has a large thermal expansion coefficient and poor thermal shock resistance, which cannot meet the requirements of the century

Method used

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  • Preparation method of Cf-ZrB2/ZrC/SiC composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] C in the present invention f -ZrB 2 The preparation method of / ZrC / SiC composite material is carried out according to the following steps successively:

[0024] (1) Preparation of carbon fiber prefabricated body: such as figure 1 As shown, two layers of twill carbon cloth 1 and one layer of ultra-thin mesh fabric 2 are laminated and formed by continuous needle punching in 1.X+1.Y mode, and the fiber volume fraction of the carbon fiber preform is controlled at 40%. .

[0025] (2) The carbon fiber preform was placed in a chemical vapor deposition furnace, and a pyrolytic carbon interface layer was prepared on the surface of the carbon fiber by a chemical vapor deposition process. The thickness of the pyrolytic carbon interface layer was controlled to 0.6 μm.

[0026] (3) Pressure impregnation: The carbon fiber preform is completely immersed in the precursor solution, and the gas in the preform is exhausted by vacuum. The vacuum degree of the vacuum exhaust during pressu...

Embodiment 2

[0031] C in the present invention f -ZrB 2 The preparation method of / ZrC / SiC composite material is carried out according to the following steps successively:

[0032] (1) Preparation of carbon fiber prefabricated body: Same as Example 1.

[0033] (2) The carbon fiber prefabricated body was placed in a chemical vapor deposition furnace, and a pyrolytic carbon interface layer was prepared on the surface of the carbon fiber by a chemical vapor deposition process. The thickness of the pyrolytic carbon interface layer was controlled to 0.5 μm.

[0034] (3) Pressure impregnation: The carbon fiber preform is completely immersed in the precursor solution, and the gas in the preform is exhausted by vacuum. The vacuum degree of the vacuum exhaust in the pressure impregnation is controlled at -0.1MPa and kept for 1.2h; The body is immersed in the prefabricated body, the boost pressure is controlled at 8MPa, kept for 1.5h, and finally cross-linked and solidified by vacuum drying; among ...

Embodiment 3

[0039] C in the present invention f -ZrB 2 The preparation method of / ZrC / SiC composite material is carried out according to the following steps successively:

[0040] (1) Preparation of carbon fiber prefabricated body: Same as Example 1.

[0041] (2) The carbon fiber prefabricated body was placed in a chemical vapor deposition furnace, and a pyrolytic carbon interface layer was prepared on the surface of the carbon fiber by a chemical vapor deposition process. The thickness of the pyrolytic carbon interface layer was controlled to 0.7 μm.

[0042](3) Pressure impregnation: The carbon fiber preform is completely immersed in the precursor solution, and the gas in the preform is exhausted by vacuum. The vacuum degree of the vacuum exhaust in the pressure impregnation is controlled at -0.1MPa and kept for 1.6h; The body is immersed in the prefabricated body, the boost pressure is controlled at 8MPa, kept for 1.3h, and finally cross-linked and solidified by vacuum drying; among t...

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Abstract

The invention relates to a preparation method of a Cf-ZrB2 / ZrC / SiC composite material, belonging to the technical field of special ceramics. The method comprises the following steps of: (1) putting a carbon fiber prefabricated body in a chemical vapor deposition furnace, and preparing a pyrolytic carbon interface layer on the surface of the carbon fiber by a chemical vapor deposition technology; (2) pressure impregnation: completely immersing the carbon fiber prefabricated body into a precursor solution, discharging gas out of the prefabricated body to be vacuum, immersing the precursor in the prefabricated body by use of high pressure, and finally performing vacuum drying and cross-linking curing; (3) high-temperature cracking: putting the impregnated and cured carbon fiber prefabricated body in a high-temperature cracking furnace, quickly heating to 1,400+ / -10 DEG C under the protection of inert atmosphere, and preserving heat for 0.5-2 hours; and (4) densifying treatment: repeating the impregnation cracking process for the carbon fiber prefabricated body after being cracked at a high temperature, until the material density at least reaches 2.0g / cm<3>. The method provided by the invention has the advantages of short period, strong adaptability and excellent material performance.

Description

technical field [0001] The present invention relates to a C f -ZrB 2 The invention relates to a preparation method of ZrC / SiC composite material, which belongs to the technical field of special ceramics. Background technique [0002] One of the most cutting-edge technologies in national defense is hypersonic technology, which mainly includes reusable spacecraft and hypersonic cruise missiles. Due to the high-speed maneuvering flight of hypersonic vehicles in the atmosphere for a long time, the requirements for aerodynamic shape are extremely strict, and new performance requirements such as long-term oxidation resistance, ultra-high temperature and zero ablation have been put forward for the heat resistance of materials. Heat-resistant materials not only need to be resistant to high temperature and erosion, but also need to withstand high temperatures of 2000 ° C or even higher for a long time in an oxidizing atmosphere. [0003] Currently used thermal protection materials...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/583C04B35/56C04B35/622
Inventor 徐鸿照周长灵刘瑞祥王艳艳李涵隋学叶
Owner SHANDONG RES & DESIGN ACADEMY OF IND CERAMICS
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