(Zr, Hf)B-SiC ceramic modified C/C composite material and preparation method thereof

A composite material and modification technology, applied in the field of C/C composite materials, can solve the problems of reduced ablation resistance, easy loss, poor bonding strength, etc., and achieve the effect of wide operating temperature range, good bonding, and high bonding strength.

Inactive Publication Date: 2019-05-03
WUHAN UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

ZrB prepared by this method 2 -The bonding strength between the ceramic coating and the substrate, ceramic coating and ceramic coating of SiC modified C/C composite material is poor, and the B produced during the ablation process 2 o 3 and SiO 2 Oxygen barr

Method used

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  • (Zr, Hf)B-SiC ceramic modified C/C composite material and preparation method thereof
  • (Zr, Hf)B-SiC ceramic modified C/C composite material and preparation method thereof
  • (Zr, Hf)B-SiC ceramic modified C/C composite material and preparation method thereof

Examples

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Effect test

Embodiment 1

[0038] A (Zr, Hf) B-SiC ceramic modified C / C composite material and a preparation method thereof. The preparation method described in this embodiment is:

[0039] (1) In an argon atmosphere, the density is 1.1 ~ 1.2g / cm 3 Put the C / C composite material into a carbonization furnace, raise the temperature to 2000-2150°C at a rate of 5-15°C / min, keep it warm for 0.5-1h, and cool naturally to obtain a high-temperature treated C / C composite material.

[0040] (2) according to zirconium powder: hafnium powder material molar ratio is 1: 0.25~0.5, described zirconium powder and described hafnium powder are mixed, obtain compound I; Described compound I is inserted in planetary ball mill, Under the condition that the rotational speed is 400-500r / min and the pressure in the ball mill tank is 500-1000Pa, ball mill for 20-24h and sieve to obtain the zirconium-hafnium alloy powder with particle size≤48μm.

[0041] (3) According to the C / C composite material treated at high temperature: t...

Embodiment 2

[0045] A (Zr, Hf) B-SiC ceramic modified C / C composite material and a preparation method thereof. The preparation method described in this embodiment is:

[0046] (1) In an argon atmosphere, the density is 1.15 ~ 1.25g / cm 3 Put the C / C composite material into a carbonization furnace, raise the temperature to 2150-2250°C at a rate of 5-15°C / min, keep it warm for 1-1.5h, and cool naturally to obtain a high-temperature treated C / C composite material.

[0047] (2) according to zirconium powder: hafnium powder material molar ratio is 1: 0.5~0.75, described zirconium powder and described hafnium powder are mixed, obtain compound I; Described compound I is inserted in planetary ball mill, Under the condition that the rotational speed is 450-550r / min and the pressure in the ball mill tank is 500-1000Pa, ball mill for 24-26 hours and sieve to obtain zirconium-hafnium alloy powder with a particle size of ≤48 μm.

[0048] (3) According to the C / C composite material treated at high temp...

Embodiment 3

[0052] A (Zr, Hf) B-SiC ceramic modified C / C composite material and a preparation method thereof. The preparation method described in this embodiment is:

[0053] (1) In an argon atmosphere, the density is 1.2 ~ 1.3g / cm 3 Put the C / C composite material into a carbonization furnace, raise the temperature to 2250-2400°C at a rate of 5-15°C / min, keep it warm for 1.5-2h, and cool naturally to obtain a high-temperature treated C / C composite material.

[0054] (2) according to zirconium powder: hafnium powder material molar ratio is 1: 0.75~1, described zirconium powder and described hafnium powder are mixed, obtain compound I; Described compound I is inserted in planetary ball mill, Under the condition that the rotational speed is 500-600r / min and the pressure in the ball mill tank is 500-1000Pa, ball mill for 26-30h and sieve to obtain the zirconium-hafnium alloy powder with particle size≤48μm.

[0055] (3) According to the C / C composite material treated at high temperature: the...

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Abstract

The invention discloses a (Zr, Hf)B-SiC ceramic modified C/C composite material and a preparation method thereof. The method includes: performing high-energy ball milling on zirconium and hafnium powders to prepare a Zr/Hf alloy, then performing reactive melt infiltration on a high-temperature treated C/C composite material and the Zr/Hf alloy to prepare a Zr/Hf carbide modified C/C composite material; then placing a powder material, containing boron and silicon, in a carbonization furnace, burying the Zr/Hf alloy modified C/C composite material in the powder material containing boron and silicon, performing thermal treatment on the materials for 1-4 h at 1800-2100 DEG C to obtain the (Zr, Hf)B-SiC ceramic modified C/C composite material. The composite material is high in ceramic content and has excellent combination between the carbon substrate and ceramic phase. Oxidized products, such as B2O3, SiO2, ZrO2 and HfO2, in the (Zr, Hf)B and SiC have excellent chemical compatibility and synergistic anti-oxidizing performance, so that the composite material has excellent anti-ablation performance.

Description

technical field [0001] The invention belongs to the technical field of C / C composite materials. The invention relates to a (Zr, Hf)B-SiC ceramic modified C / C composite material and a preparation method thereof. Background technique [0002] C / C composite material is a new type of structural material with carbon fiber or carbon fiber braid as reinforcement and pyrolytic carbon as carbon matrix. It has a series of excellent properties such as low density, high specific strength and high specific modulus. , especially at high temperature, the strength increases with the increase of temperature, low thermal expansion coefficient, ablation resistance and other advantages, so it is widely used as a high temperature structural material in the field of aerospace. However, C / C composites are easily oxidized in an aerobic environment above 450°C, causing a sharp drop in performance in all aspects. The temperature of the nose cone and the leading edge of the wing of a supersonic vehi...

Claims

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Application Information

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IPC IPC(8): C04B35/83C04B35/622
Inventor 董志军陈枫李轩科袁观明丛野张江朱辉
Owner WUHAN UNIV OF SCI & TECH
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