A method for preparing continuous carbon fiber toughened ultra-high temperature ceramic matrix composites by electrophoretic deposition

Abstract

The invention belongs to the field of ultra-high-temperature ceramic-based composite materials, and specifically relates to a method for preparing continuous carbon fiber toughened ultra-high-temperature ceramic-based composite materials by electrophoretic deposition. First, polydopamine coatings are prepared on carbon fibers; The surface of the high-temperature ceramic powder and the ultra-high-temperature ceramic powder are charged; then the charged ultra-high-temperature ceramic powder is uniformly deposited on the carbon fiber containing polydopamine coating by electrophoretic deposition technology; finally, dense continuous carbon fiber is obtained by hot pressing sintering Toughened ultra-high temperature ceramic matrix composites. Effects and benefits of the present invention: First, the ultra-high temperature ceramic powder is effectively introduced into the carbon fiber bundle, which solves the problem of difficult densification in the preparation of continuous carbon fiber toughened ultra-high temperature ceramic matrix composites; second, avoids The chemical corrosion of the carbon fiber optimizes the matrix components, obtains a good fiber-matrix interface, and improves the fracture resistance and ultra-high temperature resistance of the composite material.

Description

technical field [0001] The invention belongs to the field of ultra-high-temperature ceramic-based composite materials, and in particular relates to a method for preparing continuous carbon fiber toughened ultra-high-temperature ceramic-based composite materials by electrophoretic deposition. Background technique [0002] With the rapid development of aerospace technology, advanced technologies based on hypersonic missiles, transatmospheric vehicles, aerospace aircraft, etc. have gradually become a development trend. When flying at hypersonic speed, the aerodynamic heating will make the local surface temperature of the aircraft very high, especially the temperature of key parts such as the nose cone, wing leading edge, and fuselage belly of the aircraft will be as high as 2000 °C or more. Although traditional high-temperature-resistant materials (such as carbon fiber reinforced carbon matrix composites, carbon fiber toughened silicon carbide matrix composites, etc.) have exce...

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Problems solved by technology

[0007] The purpose of the present invention is to provide a method for preparing continuous carbon fiber toughened ultra-high temperature ceramic matrix composites by electrophoretic deposition, which aims to solve the problem of difficult preparation of continuous carbon fiber toughened ultrahigh temperature ceramic matrix composites and avoid the difficulty of fiber in the process of composite material preparation. Reactive erosion of the matrix phase and obtaining a good fiber-matrix bonding interface, thereby preparing carbon fiber toughened ultra-high temperature ceramic matrix composites with better fracture performance

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