Method for preparing carbon/carbon/silicon carbide composite material

Abstract

The invention relates to a preparation method of a carbon / carbon / silicon carbide composite material. The preparation method is characterized in that: chemical gas phase permeation technology is adopted to prepare reactive carbon atom and provide protection for carbon fiber, and is combined with the resin liquid phase dipping carbonizing technology to prepare carbon / carbon composite material through adopting a pore adjusting method of a composite material blank; moreover, the density of the obtained carbon / carbon composite material is between 1.0g / cm<3> and 1.90g / cm<3>; a method according to which the gaseous atom generated through the evaporation of solid silicon and the carbon atom in the carbon / carbon composite material are formed into SiC through chemical reaction under high temperature ranging from 1,650 DEG C to 2,200 DEG C is adopted to carry out the rapid preparation of the carbon / carbon / silicon carbide composite material. Compared with body carbon / carbon composite material, the mechanical property of the carbon / carbon / silicon carbide composite material is substantially increased to an equivalent degree and has outstanding antioxidation. Moreover, the preparation method is an engineered method which can realize the efficient preparation of a small-scale thin-wall special-shaped high-performance carbon / carbon / silicon carbide composite material.

Description

technical field [0001] The invention relates to a preparation method of a carbon / carbon / silicon carbide composite material, in particular to a liquid rocket attitude control, orbit control engine thrust chamber and a solid material linear expansion coefficient, thermal conductivity and other thermal constant measuring instrument heating element Preparation method of carbon / carbon / silicon carbide composite material. Background technique [0002] Carbon / carbon composite materials have excellent high-temperature mechanical properties and good thermal shock resistance, and have become the first choice for high-temperature thermal structural components in the fields of aviation and aerospace. However, its application is limited because it is prone to oxidation in high temperature (higher than 400°C) oxidizing environment. Improving the oxidation resistance of carbon / carbon composites has always been the focus and hotspot of research in this field. Silicon carbide (SiC)-based an...

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Problems solved by technology

The current SiC coating preparation method has problems such as difficulty in forming, pollution to the environment, or high requirements on equipment, and due to the mismatch of thermal expansion coefficients, poor bonding between the coating and the body material is a problem that must be considered. coating structure design

The use of carbon / silicon carbide composite materials is an effective way to achieve long-term oxidation resistance, but an important shortcoming of existing carbon / silicon carbide composite materials is that the production cycle is long, the preparation cost is too high, and the hydrogen chloride tail gas produced by certain preparation methods is harmful to the environment. There is pollution, and the service temperature of carbon / silicon carbide composite materials is only 1650°C, which is far lower than the service temperature limit of carbon / carbon composite materials (higher than 3000°C)

[0004] In addition to the above-mentioned common problems, the research on anti-oxidation technology of carbon / carbon composite materials in my country still focuses on basic theory or small sample test research due to its late start and backward technical level, and there is a big gap in engineering application.

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