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A high-size special-shape carbon-based composite material member and a preparing method thereof

A composite material component and special-shaped carbon technology, which is applied in the field of composite materials, can solve the problems of thin-walled carbon-based composite components that are easy to deform after standing for a long time, and carbon fiber prefabricated bodies that are easy to deform, so as to solve the problem of easy deformation and reduce the standing time , the effect of uniform performance

Active Publication Date: 2017-07-14
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the deficiencies of the prior art, the present invention provides a large-size special-shaped carbon-based composite component and its preparation method. The problem of easy deformation during the preparation process, the carbon-based composite material produced by it has the advantages of good mechanical properties, small thermal expansion coefficient, high thermal conductivity and good chemical stability.

Method used

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  • A high-size special-shape carbon-based composite material member and a preparing method thereof
  • A high-size special-shape carbon-based composite material member and a preparing method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0054] (1) The PAN-based T700 (12K) non-weft fabric produced by Toray Corporation of Japan is alternately laminated with the mesh tire, and needle-punched to a volume density of 0.45±0.02g / cm 3 , a carbon fiber prefabricated body with an outer diameter of Φ211mm, a height of 280mm, and a wall thickness of 4.5mm. The lamination method of the non-weft fabric is 0° / 45° / 90°. When needling, the needling density is 45 needles / cm 3 , The needle depth is 18mm. When laying layers, 18 layers of carbon fiber are laid on a thickness of 1 cm (that is, the total number of layers of non-weft cloth and mesh tires laid on a thickness of 1 cm is 16 layers).

[0055] (2) The carbon fiber prefabricated body is subjected to high-temperature heat treatment in a high-temperature treatment furnace, and kept at 800° C. for 30 minutes in a nitrogen atmosphere.

[0056] (3) Put the carbon fiber preform in a CVI furnace, use propylene as the main carbon source gas, and nitrogen as the carrier gas to p...

Embodiment 2

[0064] (1) The PAN-based T700 (12K) twill fabric produced by Japan Toray Co., Ltd. is alternately laminated with the mesh tire. The lamination method of the non-weft fabric is 0° / 45° / 90°, and the volume density of needle punching is 0.50g. / cm 3 Carbon fiber prefabricated body for satellite light bar. When needling, the needling density is 35 needles / cm 3 , The needle depth is 25mm. When laying layers, 14 layers of carbon fiber are laid on a thickness of 1cm.

[0065] (2) The carbon fiber prefabricated body is subjected to high-temperature heat treatment in a high-temperature treatment furnace, and kept at 800° C. for 2 hours in a nitrogen atmosphere.

[0066] (3) Put the carbon fiber preform in a CVI furnace, use propylene as the main carbon source gas, and nitrogen as the carrier gas to perform thermal gradient chemical vapor infiltration. Deposition temperature is 1200°C, propylene flow: 20L / min, nitrogen flow: 60L / min, chamber pressure: 1.0KPa, time 50 hours. Get a de...

Embodiment 3

[0074] (1) The PAN-based T700 (12K) non-weft fabric produced by Toray Corporation of Japan is alternately laminated with the mesh tire. The lamination method of the non-weft fabric is 0° / 45° / 90°, and the volume density is woven by needle punching 0.45g / cm 3 carbon fiber preforms. When needling, the needling density is 35 needles / cm 3 , The needle depth is 18mm. When laying layers, 14 layers of carbon fiber are laid on a thickness of 1cm.

[0075] (2) The carbon fiber prefabricated body is subjected to high-temperature heat treatment in a high-temperature treatment furnace, and kept at 600° C. for 2 hours in a nitrogen atmosphere.

[0076](3) Put the carbon fiber preform in a CVI furnace, use propylene as the main carbon source gas, and nitrogen as the carrier gas to perform thermal gradient chemical vapor infiltration. The deposition temperature is 1000°C, the flow rate of natural gas: 30L / min, the flow rate of nitrogen gas: 60L / min, the chamber pressure: 1.0KPa, and the t...

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Abstract

The invention relates to a high-size special-shape carbon-based composite material member and a preparing method thereof. The member includes, by mass, 20-35% of carbon fibers, 35-75% of pyrolytic carbon and 5-15% of SiC. The preparing method includes needling the continuous carbon fibers into a prefabricated blank the density of which is 0.4-0.55 g / cm<3> according to a required shape of the member; then fixing the inner and outer surfaces of the prefabricated blank by adopting a graphite mold; and then performing high-temperature thermal treatment, a first time of carbon deposition, demolding, coarse machining, a second time of carbon deposition, graphite processing, silicon vapor bathing and finish machining in order to obtain a finished product. According to the member and the method, a problem that high-size special-shape carbon-based composite material members are liable to deform in long-time standing processes and preparing processes is overcome, and the obtained product has advantages of good mechanical performance, a low thermal expansion coefficient, high thermal conductivity, good chemical stability, and the like, is suitable for industrial production, and can be applied in the field of aviation and aerospace, the field of communication and transportation, the field of biomedicine, and the like.

Description

technical field [0001] The invention relates to the technical field of composite materials; in particular, it relates to a large-size special-shaped carbon-based composite component and a preparation method thereof. Background technique [0002] Carbon-based composite materials are composite materials composed of carbon fiber skeleton and matrix (carbon-based, ceramic-based, etc.), and are structural and functional integrated engineering materials with excellent high-temperature performance. , anti-ablation, anti-space high-energy particle radiation and other advantages, so it has been greatly developed and important in the fields of aerospace, military industry, and civil materials (such as nuclear reactors, high-temperature bearings, carbon crucibles and heat sealing rings, etc.) . [0003] Taking the aerospace vehicle thermal protection system as an example, the thermal protection system of the aircraft is increasingly favoring non-metallic ceramic thermal protection. O...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83C04B35/52C04B41/87
CPCC04B35/522C04B35/83C04B41/5059C04B41/87C04B2235/77C04B41/4545
Inventor 李专肖鹏朱苏华
Owner CENT SOUTH UNIV
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