Preparation method of C/C-SiC-MoSi2 ceramic-based composite material

Abstract

A preparation method of a C/C-SiC-MoSi2 ceramic-based composite material includes the following steps: 1) dispersing silicon carbide powder and molybdenum disilicide powder in isopropyl alcohol, and performing ultrasound vibration and stirring to obtain a suspension liquid A and a suspension liquid B: 2) increasing the density of a low-density carbon fiber stereo fabric in a manner of hydrothermal permeation of glucose, and placing the fabric in a suction filtration device having a glass sand core; 3) pouring the suspension liquid A and the suspension liquid B successively into a suction filtration flat-bottom funnel to enable the suspension liquids to pass the C/C composite material completely; 4) performing a homogeneous phase hydrothermal reaction until the density is 1.2-1.5 g/cm<3>; and 5) performing thermal treatment to obtain the C/C-SiC-MoSi2 ceramic-based composite material. The composite material is moderated in density, is compact in structure, and is excellent in interface binding between a C/C interface and a SiC interface, the SiC interface and a MoSi2 interface and the C/C interface and the MoSi2 interface. The raw materials are easy to obtain. The preparation method is simple in operation, is low in cost, is environment-friendly and is pollution-free.

Description

technical field [0001] The invention belongs to the technical field of C / C composite materials, and relates to a C / C-SiC-MoSi 2 Preparation method of ceramic matrix composite material. Background technique [0002] Carbon / carbon (C / C) composites are currently the only high-temperature composite materials that can be applied at 2800 °C. Due to their excellent properties, they have broad application prospects in the aerospace field, such as low thermal expansion coefficient, low density, and High temperature, ablation resistance, high strength, high modulus and other excellent properties, especially the excellent properties that the strength and modulus increase with the increase of temperature under the condition of inert atmosphere within 2200 °C. However, C / C composites will be oxidized in an aerobic environment exceeding 370 °C, and the loss of oxidized mass will lead to a decrease in its strength, which limits its application range, especially in high temperature or humi...

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Problems solved by technology

Precursor impregnation cracking method has a long cycle of multiple impregnation processes, which is prone to shrinkage cracks and high cost (2009)3438–3443.], the matrix densification rate of the composite material prepared by chemical vapor infiltration method is low, the production cycle is long, and the stability of the composite material is low [J.Yin, H.B. Zhang, X. Xiong, J. Zuo, H.J. Tao, Ablation properties of C / C–SiC composite tested on an archeater, Solid State Sci.13 (2011) 2055–2059.], the composite material prepared by fusion siliconizing method is easy to reduce the strength of fiber reinforcement, and the cost is too high [SeYoungKim, etal.Wear-mechanicalpropertiesoffiller- addedliquidsiliconinfiltrationC / C–SiCcompositesMaterialsandDesign[J],44(2013)107–113.], and the composite material prepared by reactive melt impregnation method has great damage to the carbon fiber, resulting in low mechanical properties and poor fracture toughness of the composite material[Z.Q.Li, H.J.Li, S.Y.Zhang, J.Wang, W.Li, F.J.Sun, Effectofreactionmeltinfiltrationtemperatureontheablationpropertiesof2DC / C–SiC–ZrCcomposites, Corros.Sci.58(2012)12–19.]

And the method that adopts vacuum filtration-homogeneous hydrothermal method to prepare carbon / carbon-high temperature resistant ceramic composite material has not yet been reported

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