Carbon fiber reinforced zirconium carbide composite material and preparation method thereof

Abstract

The invention discloses a carbon fiber reinforced zirconium carbide composite material and a preparation method thereof. The carbon fiber reinforced zirconium carbide composite material uses a carbon fiber prefabricated part as a reinforcement body and zirconium carbide as a matrix; the volume fraction of zirconium carbide in the carbon fiber reinforced zirconium carbide composite material It is 25% to 43%, and the opening rate is 5% to 10%. The preparation method comprises seven steps of vacuum impregnating zirconium source, crosslinking and solidifying zirconium source, vacuum impregnating carbon source, crosslinking and solidifying carbon source, densification, high temperature reaction and redensification. The preparation method of the present invention has the advantages of simple preparation process, cheap and easy-to-obtain raw materials, short preparation period, and low preparation cost, and the prepared carbon fiber reinforced zirconium carbide composite material has the advantages of high ZrC content, low porosity, high density, etc., and The material has high strength and excellent mechanical properties, and is one of the important candidate materials for ultra-high temperature thermal protection of hypersonic aircraft.

Description

technical field [0001] The invention belongs to the technical field of preparation of ultra-high temperature thermal protection structures, and in particular relates to a carbon fiber reinforced zirconium carbide composite material and a preparation method thereof. Background technique [0002] Hypersonic aircraft has the characteristics of high flight altitude, fast speed, strong penetration capability, and difficult detection. It can strike various time-sensitive targets tens of thousands of kilometers away in a short period of time, and has extremely important military value and significance. A hypersonic vehicle needs to have a high lift-to-drag ratio in order to be able to fly from low-speed transversal and supersonic acceleration to cruising flight above 5 Ma, and the shape of the high-lift-to-drag ratio requires the shape of the nose cone and the leading edge of the wing to have a small radius of curvature, and must meet zero ablation / microablation requirements. Ex...

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Problems solved by technology

However, this process cannot introduce a large amount of ZrO 2 , because ZrO 2 If the content is too high, it will affect the subsequent CVI infiltration process, which may cause too many internal voids to form a "hollow" structure and cannot be dense.

Therefore, this method cannot obtain C / C-ZrC materials with high ZrC content. The highest ZrC content of C / C-ZrC materials in reports is only about 14wt%, which is converted into a volume content of less than 5%.

[0007] Therefore, in view of the shortcomings in the prior art, such as complex synthesis of precursors, low ceramic yield, long composite material preparation cycle, high cost, or low ZrC introduction efficiency and low content, it is urgent to develop a simple and simple preparation process. Preparation method of carbon fiber reinforced zirconium carbide composite material with cheap and easy-to-obtain raw materials, short preparation cycle and low preparation cost

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