C/ZrC composite material prepared on basis of vapor infiltration reaction, preparation method thereof and equipment for process

Abstract

The invention discloses a C / ZrC composite material prepared on the basis of vapor infiltration reaction. The C / ZrC composite material adopts zirconium carbide as a matrix and adopts a carbon fiber prefabricated body as an enhanced phase. For the C / ZrC composite material, the density is 1.98-4.25g / cm<3>, the aperture ratio is 6%-18% and the content of metal zirconium is below 0.5wt%. A preparation method comprises the following steps of: in preparation, firstly forming a fiber prefabricated body, then preparing a fiber protective coating and a porous C / C prefabricated body, carrying out high-temperature treatment on the prepared porous C / C prefabricated body in the inert atmosphere, finally putting the metal zirconium at the bottom of a graphite crucible, putting the C / C prefabricated body above the metal zirconium, heating under the vacuum condition, enabling zirconium steam to be volatilized and carry out vapor impregnation reaction with the C / C prefabricated body so as to obtain a product. Self-made vapor impregnation equipment is adopted in preparation. The invention has the advantages that the period is short, the cost is low, the high-temperature resistance of a product is good, the mechanical property is excellent, the residual amount of metal is minimum and the like.

Description

technical field [0001] The invention belongs to the technical field of preparation of an ultra-high temperature thermal protection structure, and in particular relates to a preparation method of a C / ZrC ultra-high temperature ceramic matrix composite material. Background technique [0002] Hypersonic vehicles have become the main development direction of new hypersonic weapon systems and aerospace, and will play an important role in future national security and development. With the increase of the flight speed of hypersonic vehicles, the demand for ultra-high temperature resistant and ablation-resistant materials is becoming more and more urgent. The existing materials can no longer meet the needs of the development of thermal protection systems and propulsion systems of hypersonic vehicles. It is necessary to develop a new generation of resistant materials. Ultra-high temperature, anti-ablation, anti-thermal shock, high reliability new material. [0003] Ultra-high temper...

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Problems solved by technology

National University of Defense Technology adopts Zr 2 The C / ZrC composite material was prepared by melting reaction of Cu alloy and Si-Zr alloy with porous C / C composite body. The lower reaction temperature of alloy infiltration process has little damage to the fiber, but the residual Cu or Si in the product after the reaction affects the material. high temperature resistance

At home and abroad, there are competing studies on the preparation of C / ZrC composites by metal zirconium liquid phase fusion infiltration reaction method, mainly because of its short process cycle, low cost, and the ability to prepare components with net size and complex shape, but this process also has shortcomings: first, The reaction is carried out through the high-temperature melt, the reaction speed is fast, and it is difficult to control the reaction time, reaction amount, and internal penetration degree, resulting in the uniformity of the product structure and the consistency of performance cannot be guaranteed; secondly, the high-temperature melt reacts with the matrix at the same time , will inevitably react with the fiber, resulting in a decrease in mechanical properties; again, a certain amount of metal will remain in the composite material prepared by the melting reaction method, which will affect the high temperature stability and mechanical properties of the composite material to a certain extent; finally, the metal melting The osmotic reaction method always inevitably leaves some metal on the surface, which requires subsequent mechanical processing or high-temperature treatment, which increases the complexity of the process and cannot achieve the effect of net shape

At present, the research reports on the preparation of C / MC composites by gas-phase metal impregnation of C / C substrates mainly focus on the preparation of C / SiC composites by the gas-phase silicon infiltration process, and the research on the preparation of C / ZrC composites by the gas-phase zirconium infiltration reaction method is currently Not yet reported

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