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A kind of c/c-sic-cu composite material and its preparation method and application

A composite material, c-sic-cu technology, applied in the field of design and preparation of thermal protective materials, can solve the problems that cannot fully meet the requirements of aircraft use, and achieve the effect of superior performance

Active Publication Date: 2021-08-31
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the ablation transition zone, molten SiO2 can bridge the defects such as cracks and pores of the material, prevent the oxidizing atmosphere from entering the interior of the material, and make the material exhibit excellent ablation resistance. The use temperature of traditional metal materials is close to its limit and cannot fully meet the requirements. aircraft requirements

Method used

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  • A kind of c/c-sic-cu composite material and its preparation method and application
  • A kind of c/c-sic-cu composite material and its preparation method and application
  • A kind of c/c-sic-cu composite material and its preparation method and application

Examples

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Effect test

Embodiment 1

[0041] A C / C-SiC-Cu composite material, which is composed of C fiber, C matrix, SiC matrix and Cu alloy, is characterized in that C, SiC, Cu three-phase coexistence. The volume fraction of the C fiber is 26%, the volume fraction of the C matrix is ​​11.8%, the volume fraction of the SiC matrix is ​​28%, the volume fraction of the Cu matrix is ​​8.5%, and the rest are evenly distributed of pores.

[0042] In this embodiment, the preparation of the designed C / C-SiC-Cu composite material includes the steps in the following order:

[0043] Step 1, preparation of carbon fiber prefabricated body:

[0044] Step 1.1. Arrange long carbon fiber tows in parallel and evenly in a certain direction. After dipping and coating, weave certain fiber filaments at a certain interval in the weft direction, and lock the edge of the non-weft cloth to ensure To ensure the integrity of the weft-free fabric;

[0045] Step 1.2, select chopped carbon fiber bundles of different lengths according to a ...

Embodiment 2

[0053] A C / C-SiC-Cu composite material, which is composed of C fiber, C matrix, SiC matrix and Cu alloy, is characterized in that C, SiC, Cu three-phase coexistence. The volume fraction of the C fiber is 26%, the volume fraction of the C matrix is ​​27.1%, the volume fraction of the SiC matrix is ​​20%, and the volume fraction of the Cu matrix is ​​8.5%.

[0054] In this embodiment, the preparation of the designed C / C-SiC-Cu composite material includes the steps in the following order:

[0055] Step 1, preparation of carbon fiber prefabricated body:

[0056] Step 1.1. Arrange the long carbon fiber tows in parallel and evenly in a certain direction. After dipping and coating, weave some kind of fiber filaments at a certain interval in the weft direction, and lock the edge of the non-weft cloth to ensure To ensure the integrity of the weft-free fabric;

[0057] Step 1.2, select chopped carbon fiber bundles of different lengths according to a certain ratio, form a single fiber...

Embodiment 3

[0065] A C / C-SiC-Cu composite material, which is composed of C fiber, C matrix, SiC matrix and Cu alloy, is characterized in that C, SiC, Cu three-phase coexistence. The volume fraction of the C fiber is 26%, the volume fraction of the C matrix is ​​27.1%, the volume fraction of the SiC matrix is ​​13%, and the volume fraction of the Cu matrix is ​​7.4%.

[0066] In this embodiment, the preparation of the designed C / C-SiC-Cu composite material includes the steps in the following order:

[0067] Step 1, preparation of carbon fiber prefabricated body:

[0068] Step 1.1. Arrange the long carbon fiber tows in parallel and evenly in a certain direction. After dipping and coating, weave some kind of fiber filaments at a certain interval in the weft direction, and lock the edge of the non-weft cloth to ensure To ensure the integrity of the weft-free fabric;

[0069] Step 1.2, select chopped carbon fiber bundles of different lengths according to a certain ratio, form a single fiber f...

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Abstract

The invention relates to a C / C-SiC-Cu composite material and a preparation method and application thereof. The C / C-SiC-Cu ceramic matrix composite material is composed of C fiber, C matrix, SiC matrix and Cu alloy, the C matrix is ​​coated on the C fiber, the SiC matrix is ​​coated on the C matrix, and the The Cu alloy composition described above is in contact with the SiC matrix and forms a metallurgical bond. The preparation method is as follows: the three phases of C, SiC and Cu coexist by combining the chemical vapor infiltration method and the pressure infiltration method. The composite material designed and prepared by the invention has excellent properties such as high strength, high temperature resistance, oxidation resistance, thermal shock resistance and ablation resistance. It is particularly suitable for thermal protection components, especially for thermal protection components used on aircraft.

Description

technical field [0001] The invention belongs to the technical field of thermal protection material design and preparation, and in particular relates to a C / C-SiC-Cu composite material and a preparation method and application thereof. Background technique [0002] As the commanding heights of the future aviation field, the hypersonic vehicle has a technological "heat wave" sweeping the world. The new type of hypersonic speed has the characteristics of fast response speed, strong defense penetration capability, and great destructiveness. The huge military value and potential commercial value make it widely valued and deeply studied by the world's aerospace powers. Sufficiently advanced thermal protection technology can allow the aircraft to glide continuously at hypersonic speeds at a specific altitude. Due to the harsh flight environment that the aircraft is subjected to during re-entry flight, and with the improvement of the performance of the aircraft, higher requirements...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C22C47/06C22C47/04C22C47/12C22C49/02C22C49/14C22C101/10C22C121/02
CPCC22C47/04C22C47/06C22C47/12C22C49/02C22C49/14
Inventor 尹健熊翔张红波张欢徐亚楠王培陈招科
Owner CENT SOUTH UNIV
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