Cf/Hf[x]Zr[1-x]C-SiC composite material and preparation methods thereof

A technology of hfxzr1-xc-c and composite materials, which is applied in the field of ceramic matrix composite materials, can solve the problems of poor thermal shock resistance, poor oxidation resistance, and low fracture toughness, and achieve improved ablation resistance and excellent burning resistance Corrosion properties, the effect of improving mechanical properties

Active Publication Date: 2016-10-12
NAT UNIV OF DEFENSE TECH
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  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

Ultra-high temperature ceramics (UHTC) refer to transition metal carbides, borides, and nitrides with a melting point exceeding 3000 ° C, such as ZrB 2 , HfB 2 , TaC, HfC, NbC, ZrC, HfN, etc. However, the inherent br

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  • Cf/Hf[x]Zr[1-x]C-SiC composite material and preparation methods thereof
  • Cf/Hf[x]Zr[1-x]C-SiC composite material and preparation methods thereof
  • Cf/Hf[x]Zr[1-x]C-SiC composite material and preparation methods thereof

Examples

Experimental program
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Embodiment 1

[0042] A kind of Cf / Hf of the present invention 0.5 Zr 0.5 C-SiC composites, including carbon fiber preforms, SiC matrix and Hf 0.5 Zr 0.5 C matrix, the Hf 0.5 Zr 0.5 The C matrix and the SiC matrix are evenly filled in the pores of the carbon fiber preform.

[0043] In this example, Hf 0.5 Zr 0.5 The volume fraction of the C matrix is ​​16%, the volume fraction of the SiC matrix is ​​20%, and the open porosity is 14.4vol%.

[0044] The Cf / Hf of the above-mentioned present embodiment 0.5 Zr 0.5 The preparation method of C-SiC composite material, comprises the following steps:

[0045] (1) Preparation of Hf 0.5 Zr 0.5 C and SiC ceramic precursor solutions:

[0046] Mix the metal source, citric acid monohydrate, ethylene glycol and distilled water with a molar ratio of 1:1:4:200 and stir and dissolve at room temperature. After the dissolution is complete, the Hf 0.5 Zr 0.5 C ceramic precursor solution, wherein, metal source is ZrOCl 2 ·8H 2 O and HfOCl 2 ·8H 2 ...

Embodiment 2

[0056] A kind of Cf / Hf of the present invention 0.7 Zr 0.3 C-SiC composites, including carbon fiber preforms, SiC matrix and Hf 0.7 Zr 0.3 C matrix, the Hf 0.7 Zr 0.3 The C matrix and the SiC matrix are evenly filled in the pores of the carbon fiber preform.

[0057] In this example, Hf 0.7 Zr 0.3 The volume fraction of the C matrix is ​​14%, the volume fraction of the SiC matrix is ​​22%, and the open porosity is 13.5vol%.

[0058] The Cf / Hf of the above-mentioned present embodiment 0.7 Zr 0.3 The preparation method of C-SiC composite material, comprises the following steps:

[0059] (1) Preparation of Hf 0.7 Zr 0.3 C and SiC ceramic precursor solutions:

[0060] Mix the metal source, citric acid monohydrate, ethylene glycol and distilled water with a molar ratio of 1:2:2:100 and stir to dissolve at room temperature. After the dissolution is complete, the Hf 0.7 Zr 0.3 C ceramic precursor solution, wherein, metal source is ZrOCl 2 ·8H 2 O and HfOCl 2 ·8H 2 O...

Embodiment 3

[0070] A kind of Cf / Hf of the present invention 0.5 Zr 0.5 C-SiC composites, including carbon fiber preforms, SiC matrix and Hf 0.5 Zr 0.5 C matrix, the Hf 0.5 Zr 0.5 The C matrix and the SiC matrix are evenly filled in the pores of the carbon fiber preform.

[0071] In this example, Hf 0.5 Zr 0.5 The volume fraction of the C matrix is ​​16%, the volume fraction of the SiC matrix is ​​28%, and the open porosity is 4.5vol%.

[0072] The Cf / Hf of the above-mentioned present embodiment 0.5 Zr 0.5 The preparation method of C-SiC composite material, comprises the following steps:

[0073] (1) Preparation of Hf 0.5 Zr 0.5 C ceramic precursor solution:

[0074] Mix the metal source, citric acid monohydrate, ethylene glycol and distilled water with a molar ratio of 1:1:4:200 and stir and dissolve at room temperature. After the dissolution is complete, the Hf 0.5 Zr 0.5 C ceramic precursor solution, wherein, metal source is ZrOCl 2 ·8H 2 O and HfOCl 2 ·8H 2 O mixture,...

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Abstract

The invention discloses a Cf/Hf[x]Zr[1-x]C-SiC composite material and preparation methods thereof. The composite material comprises a carbon fiber fabricated part, an SiC substrate and an Hf[x]Zr[1-x]C substrate, wherein x is larger than 0 and smaller than 1, and the Hf[x]Zr[1-x]C substrate and the SiC substrate are uniformly filled in the holes of the carbon fiber fabricated part. One preparation method comprises the following steps that (1), a Cf/Hf[x]Zr[1-x]C blank is prepared; (2) the Cf/Hf[x]Zr[1-x]C-SiC composite material is prepared. The other preparation method comprises the following steps that (1), a Cf/Hf[x]Zr[1-x]C blank is prepared; (2) a Cf/Hf[x]Zr[1-x]C-C blank is prepared; (3) the Cf/Hf[x]Zr[1-x]C-SiC composite material is prepared. The Cf/Hf[x]Zr[1-x]C-SiC composite material has the advantages that the material is low in cost, ablative-resistant, excellent in mechanical property and oxidation resistance and the like, and at the same time, the preparation methods are simple, and the contents of the substrates are easy to control.

Description

technical field [0001] The invention belongs to the field of ceramic matrix composite materials, in particular to a Cf / Hf x Zr 1-x C-SiC composite material and its preparation method. Background technique [0002] The thermal protection system of hypersonic vehicle nose cone, wing leading edge, rocket engine combustion chamber and other components is facing increasingly harsh working environment, which urgently requires the development and application of new ultra-high temperature resistant materials. Existing high-temperature-resistant materials such as refractory metals, graphite materials, C / C, and Cf / SiC composite materials can no longer meet the application requirements, so new material systems with ultra-high temperature resistance, ablation resistance, and oxidation resistance have been developed for new spacecraft development is of great significance. Therefore, researchers turned their attention to ultra-high temperature ceramic materials. Ultra-high temperature...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/56C04B35/571
CPCC04B35/5622C04B35/571C04B35/806C04B2235/5248C04B2235/5252C04B2235/614C04B2235/616
Inventor 刘荣军严春雷曹英斌张长瑞王衍飞龙宪海王思青李斌
Owner NAT UNIV OF DEFENSE TECH
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