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Continuous fiber-reinforced zirconium carbide based composite material and preparation method thereof

A composite material and zirconium carbide-based technology, which is applied in the field of continuous fiber reinforced zirconium carbide-based composite materials and their preparation, can solve the problems of insufficient thermal shock resistance and oxidation resistance, and achieve the advantages of comprehensive performance and uniform introduction.

Active Publication Date: 2015-09-16
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to solve the problems of the existing high-temperature thermal protection materials while satisfying thermal shock resistance and oxidation resistance, and to propose a continuous fiber-reinforced zirconium carbide-based composite material and its preparation method. Excellent comprehensive performance, the method has a simple process and is suitable for engineering applications

Method used

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preparation example Construction

[0020] A method for preparing a continuous fiber reinforced zirconium carbide matrix composite material, the specific steps are:

[0021] 1) The continuous fiber prefabricated body is subjected to interface carbon sinking treatment at a temperature of 950-1050°C and kept for 1-2 hours for 2-3 times in total to obtain a low-density fiber skeleton blank;

[0022] 2) Mix zirconium carbide powder and silicon carbide powder at a mass ratio of 4:1 to 3:2, use absolute ethanol as a dispersant, use ultrasonic dispersion, high-speed ball milling and rotary evaporator to evaporate and dry, and the ultrasonic dispersion time is 1-3:2. 2h, the ball milling time is 8-10h, and the mixed ceramic powder is obtained;

[0023] 3) Mix the ceramic powder obtained in step 2) with phenolic resin and absolute ethanol, the mass ratio of ceramic powder to phenolic resin is 1:1~3, and the mass ratio of ceramic powder to absolute ethanol is 1:0.5~ 2. After high-speed mechanical stirring, ultrasonic di...

Embodiment 1

[0028] A continuous fiber-reinforced zirconium carbide-based composite material, which uses T700 carbon fiber needle-punched prefabricated body as the skeleton, carbon fiber mass fraction 30%, carbon fiber surface interface matrix carbon layer mass fraction 30%, zirconium carbide, silicon carbide average particle size The diameters are all 0.5-2 μm, the mass fraction of zirconium carbide is 30%, and the mass fraction of silicon carbide is 10%.

[0029] A method for preparing a continuous fiber reinforced zirconium carbide matrix composite material, the specific steps are:

[0030] 1) Select a prefabricated body with a size of 150mm×150mm×100mm for interfacial deposition of a carbon layer. The treatment temperature is 1050°C, and the temperature is kept for 2 hours. The thickness of the deposited carbon layer is 5-10 μm, and the low-density fiber is obtained. skeleton blank,

[0031] 2) Mix zirconium carbide powder and silicon carbide powder with an average particle size of 0....

Embodiment 2

[0038] A continuous fiber-reinforced zirconium carbide-based composite material, which uses T700 carbon fiber needle-punched prefabricated body as the skeleton, the mass fraction of carbon fiber is 30%, the mass fraction of carbon fiber surface interface layer is 30%, and the average particle size of zirconium carbide and silicon carbide is 0.5 ~2 μm, the mass fraction of zirconium carbide is 25%, and the mass fraction of silicon carbide is 15%.

[0039] A method for preparing a continuous fiber reinforced zirconium carbide matrix composite material, the specific steps are:

[0040] 1) Select a prefabricated body with a size of 150mm×150mm×100mm for interfacial deposition of a carbon layer. The treatment temperature is 1050°C, and the temperature is kept for 2 hours. The thickness of the deposited carbon layer is 5-10 μm, and the low-density fiber is obtained. Skeleton blank;

[0041] 2) Mix zirconium carbide powder and silicon carbide powder with an average particle size of ...

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Abstract

The present invention relates to a continuous fiber-reinforced zirconium carbide based composite material and a preparation method thereof, and belongs to the technical field of high temperature thermal protection materials. According to the present invention, the prepared continuous fiber-reinforced zirconium carbide based composite material has excellent performances of lightweight, high performance resistance, anti-oxidation property and the like, the density is 1.9-2.2 g / cm<3>, the tensile strength is 96-150 MPa, the bending / compressive strength is 130-180 MPa, the mass loss under the 2000 DEG C aerobic environment only is 10<-4> g / cm<2>s magnitude, and the composite material shows the good comprehensive performance advantages, and can be applied in novel high hypersonic aircrafts, high-speed re-entry vehicles, reusable orbital maneuvering aircrafts, advanced power systems, and other high temperature thermal protection systems.

Description

technical field [0001] The invention relates to a continuous fiber-reinforced zirconium carbide-based composite material and a preparation method thereof. A continuous fiber-reinforced composite material is obtained by using a continuous carbon fiber prefabricated body as a skeleton, zirconium carbide and silicon carbide multicomponent components as a matrix, and adopting a method of liquid phase impregnation and cracking. A zirconium carbide-based composite material belongs to the technical field of high-temperature thermal protection materials. Background technique [0002] With the competition of international military science and technology and the rapid development of aerospace technology, the pursuit of lightweight, efficient, fast and reliable performance of spacecraft is becoming more and more intense, which will inevitably pose a big challenge to the field of materials. High-temperature thermal protection materials refer to a class of materials that can maintain goo...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/56C04B35/622
Inventor 冯志海徐林张寅李炜宋永忠程家李兴超樊桢
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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