Preparation method for matricial ultra-temperature ceramic composite material of zirconium boride-silicon carbide

A technology of ultra-high temperature ceramics and composite materials, which is applied in the field of preparation of composite materials, and can solve problems such as low strength and fragility

Inactive Publication Date: 2010-11-24
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide a method for preparing a zirconium boride-silicon carbide based ultra-high temperature ceramic

Method used

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  • Preparation method for matricial ultra-temperature ceramic composite material of zirconium boride-silicon carbide
  • Preparation method for matricial ultra-temperature ceramic composite material of zirconium boride-silicon carbide
  • Preparation method for matricial ultra-temperature ceramic composite material of zirconium boride-silicon carbide

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specific Embodiment approach 1

[0009] Specific embodiment one: the preparation method of the zirconium boride-silicon carbide layered ultra-high temperature ceramic composite material in this embodiment is as follows: 1. 20 parts by volume of α-SiC powder and 80 parts of ZrB 2 Powder mixing, adding absolute ethanol, the amount of absolute ethanol added is α-SiC powder, ZrB 2 The volume percentage of the total powder and absolute ethanol is 70%~75%, and then conduct constant temperature ball milling at 20~30°C for 10~15h, and then at 70~80°C, the speed is 30r / min~60r / min Dry and sieve to obtain ZrB with a particle size of 200-300 mesh 2 -20%volSiC powder; 2. By volume, 30 parts of α-SiC powder and 70 parts of ZrB 2 Powder mixing, adding absolute ethanol, the amount of absolute ethanol added is α-SiC powder, ZrB 2 The volume percentage of the total powder and absolute ethanol is 70%~75%, and then conduct constant temperature ball milling at 20~30°C for 10~15h, and then at 70~80°C, the speed is 30r / min~60r / m...

specific Embodiment approach 2

[0013] Embodiment 2: This embodiment is different from Embodiment 1 in that the release agent described in step 3 is boron nitride. Others are the same as in the first embodiment.

specific Embodiment approach 3

[0014] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that the addition of absolute ethanol in step one is α-SiC powder, ZrB 2 The volume percentage of powder and absolute ethanol total amount is 72%. Others are the same as those in the first or second embodiment.

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Abstract

The invention provides a preparation method for matricial ultra-temperature ceramic composite material of zirconium boride-silicon carbide, which relates to a preparation method of a composite material. The invention solves the problems of easy frangibility and low strength of the existing zirconium boride-silicon carbide based composite material. The preparation method comprises the following steps: respectively preparing ZrB2-20%volSiC powders and ZrB2-30%volSiC powders; symmetrically and alternatively laminating the ZrB2-20%volSiC powders and the ZrB2-30%volSiC powders into a graphite mould to obtain a green body; prepressing the green body; and maintaining pressure for 60 min under the condition of 190 DEG C and 30 MPa to obtain the composite material of the invention. Strength of the matricial ultra-temperature ceramic composite material of zirconium boride-silicon carbide in the invention is 1.57-2.36 times that of the zirconium boride-silicon carbide (ZrB2-20 parts of SiC) based composite material; and fracture toughness of the matricial ultra-temperature ceramic composite material of zirconium boride-silicon carbide in the invention can be increased by 17%-46% compared with that of the zirconium boride-silicon carbide (ZrB2-20 parts of SiC) based composite material.

Description

technical field [0001] The invention relates to a preparation method of a composite material. Background technique [0002] The high-temperature strength, oxidation resistance and thermal shock resistance of ultra-high temperature ceramic matrix composites make them suitable for extreme environments including hypersonic long-duration flight, atmospheric re-entry, trans-atmospheric flight and rocket propulsion systems. Various key parts or components such as nose cone, wing leading edge, engine hot end, etc. Materials capable of meeting such demanding performance requirements are mainly concentrated in multi-component composite ultra-high temperature ceramic material systems composed of high-melting point borides. Oxidation properties. In the past few years, it has been recognized that the addition of silicon carbide can significantly improve the mechanical properties and oxidation resistance of zirconium boride ceramics. Many foreign studies have focused on a variety of zi...

Claims

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Application Information

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IPC IPC(8): C04B35/58C04B35/622
Inventor 王玉美杨强高明洪长青
Owner HARBIN INST OF TECH
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