C-C-SiC-ZrC ceramic matrix composite and preparation method thereof

Abstract

The invention discloses a C-C-SiC-ZrC ceramic matrix composite and a preparation method thereof. The C-C-SiC-ZrC ceramic matrix composite comprises C fiber, a C matrix, an SiC matrix and a ZrC matrix, and is characterized in that the SiC matrix exists between a C / C framework and the ZrC matrix. The preparation method comprises the steps as follows: the C fiber is woven or laminated to form an enhancement structure, pyrolytic carbon is deposited with a chemical vapor infiltration method, then the synthesized C / C framework is subjected to high-temperature graphitization, an SiC densified composite is introduced through liquid-phase infiltration and pyrolysis of polycarbosilane, boron-containing phenolic resin is soaked, C is formed through pyrolysis, metal Zr is infiltrated with an infiltration method, and high-temperature heat treatment is performed to obtain the C-C-SiC-ZrC ceramic matrix composite. The C-C-SiC-ZrC ceramic matrix composite has excellent performance including high strength, superhigh temperature resistance, antioxidation, thermal shock resistance and the like.

Description

technical field [0001] The invention relates to a ceramic matrix composite material and a preparation method thereof, in particular to a C / C-SiC-ZrC ceramic matrix composite material and a preparation method thereof. technical background [0002] The long-term flight of hypersonic vehicles, atmospheric reentry, transatmospheric flight and rocket propulsion system put forward extremely strict requirements on high-temperature thermal structural materials. In these environments, high-temperature thermal structural materials are not only required to withstand 2000 ° C or even higher It also has to withstand the scour of high-speed air flow and the corrosion of oxidizing gas. Existing C / SiC composite materials and C / C composite materials can no longer meet the requirements for the use of supersonic aircraft nose cones, wing leading edges, and long-life engine combustion chambers. The C / SiC composite material is mainly limited by its poor temperature resistance. The optimum opera...

AI Technical Summary

Problems solved by technology

However, the mechanical properties of the material are significantly reduced due to the fact that the metal Zr is easy to damage the C fibers during the infiltration process.