This invention provides a high-parameter SiC / SiC
ceramic matrix
composite material, relating to the field of
aerospace high-temperature structural materials. This high-parameter SiC / SiC
ceramic matrix
composite material is composed of a
SiC fiber preform, an interface phase, and a SiC matrix; the interface phase is a BN layer or a PyC+BN composite gradient layer; the
SiC fiber preform adopts a 3D orthogonal braided or needle-punched structure, with a
fiber volume fraction of 45%–55%; the SiC matrix is prepared by a CVI+PIP
composite process, with a matrix
porosity ≤5%. The preparation method includes four main steps:
SiC fiber preform preparation, interface phase deposition, SiC matrix densification, and environmental barrier
coating. By optimizing the preform braiding structure, interface phase type, and
matrix composition, combined with specific preparation processes, the
composite material meets the requirements of high mechanical properties, high high-temperature
oxidation resistance,
high density, and high
thermal conductivity. This preparation method, through CVI+PIP
composite process optimization, nano-dispersed phase addition, and gradient interface phase design, overcomes existing process bottlenecks and achieves the industrial-scale preparation of high-performance composite materials.