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Preparation method for thermo-structure composite capable of resisting temperature of 1800 DEG C

A composite material and carbon composite material technology, which is applied in the field of preparation of thermal structural composite materials with a temperature resistance of 1800 °C, can solve the problems of high oxidation resistance and mechanical properties, and achieves the improvement of overall mechanical properties, low density and good fluidity. Effect

Active Publication Date: 2017-05-31
BEIHANG UNIV
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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 provide a method for preparing a thermal structural composite material with a temperature resistance of 1800°C, aiming to solve the problem that the composite material in the prior art cannot have both high oxidation resistance and mechanical properties

Method used

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  • Preparation method for thermo-structure composite capable of resisting temperature of 1800 DEG C
  • Preparation method for thermo-structure composite capable of resisting temperature of 1800 DEG C
  • Preparation method for thermo-structure composite capable of resisting temperature of 1800 DEG C

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specific Embodiment 1

[0031] Such as figure 1 with figure 2 As shown, the embodiment of the present invention provides a method for preparing a thermal structural composite material with a temperature resistance of 1800°C, including:

[0032] Step S101, preparing a carbon fiber preform;

[0033] Step S102, preparing a pyrolytic carbon interface layer on the carbon fiber prefabricated body to obtain a carbon fiber reinforced carbon composite material;

[0034] Step S103, performing high-temperature heat treatment on the carbon fiber reinforced carbon composite material;

[0035] Step S104, preparing a silicon carbide interface layer on the carbon fiber reinforced carbon composite material to obtain a carbon fiber reinforced carbon-silicon carbide composite material;

[0036] Step S105, preparing submicron lanthanum hexaboride powder;

[0037] Step S106, dissolving polycarbosilane, zirconium diboride precursor, and submicron lanthanum hexaboride powder in toluene solution to prepare an impregnat...

specific Embodiment 2

[0066] An embodiment of the present invention provides a method for preparing a thermal structural composite material with a temperature resistance of 1800°C, the method comprising:

[0067] 1) Prepare a carbon fiber prefabricated body, the prefabricated body is composed of two-dimensional carbon cloth laminates, and the carbon fiber volume fraction is 40vol.%;

[0068] 2) Preparation of pyrolytic carbon (PyC) interface layer by chemical vapor deposition method, ethylene or methane as carbon source, hydrogen as carrier gas, argon as dilution gas, set appropriate furnace pressure, source gas / carrier gas flow ratio, gas Flow rate and temperature, deposition time 6 ~ 8h to get C / C composite material;

[0069] 3) Perform high temperature heat treatment at 1800°C on the above C / C composite material for 2 hours;

[0070] 4) The SiC interface layer was prepared by chemical vapor deposition method, using trichloromethylsilane (CH 3 SiCl 3 ) as the gas source for chemical vapor depo...

specific Embodiment 3

[0078] An embodiment of the present invention provides a method for preparing a thermal structural composite material with a temperature resistance of 1800°C, the method comprising:

[0079] 1) Prepare a carbon fiber prefabricated body, the prefabricated body is a three-dimensional needle-punched carbon felt, and the volume fraction of carbon fiber is 35vol.%;

[0080] 2) Preparation of pyrolytic carbon (PyC) interface layer by chemical vapor deposition method, ethylene or methane as carbon source, hydrogen as carrier gas, argon as dilution gas, set appropriate furnace pressure, source gas / carrier gas flow ratio, gas Flow rate and temperature, deposition time 6 ~ 8h to get C / C composite material;

[0081] 3) Carry out heat treatment on the low-density C / C porous composite material, the heat treatment temperature is 1900°C, and the time is 1.5h;

[0082] 4) The SiC interface layer was prepared by chemical vapor deposition method, using trichloromethylsilane (CH 3 SiCl 3 ) as...

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Abstract

The invention provides a preparation method for a thermo-structure composite capable of resisting a temperature of 1800 DEG C. A carbon fiber reinforced carbon-zirconium diboride-silicon carbide-lanthanum hexaboride composite, which is prepared with carbon fiber as a reinforcement body and a high-temperature-resistant multiphase ceramic composite as a matrix, integrates the advantages of both a carbon fiber reinforced carbon composite and the multiphase ceramic composite. The thermo-structure composite prepared by the preparation method has the advantages of low density, excellent mechanical property, high oxidation resistance and high ablation resistance; carbon, zirconium diboride, silicon carbide and lanthanum hexaboride in the matrix coexist; in the high temperature oxidation process, the substances are oxidized in sequence to generate a protective film for blocking oxygen diffusion and seeping, and a mechanism for alternately or jointly suppressing oxygen is formed to protect reinforced fibers from oxidation erosion; and through combination of zirconium diboride, silicon carbide and lanthanum hexaboride, the mechanical property and high temperature oxidation resistance of the thermo-structure composite are greatly improved.

Description

technical field [0001] The invention relates to the technical field of composite materials, in particular to a method for preparing a thermal structural composite material with a temperature resistance of 1800°C. Background technique [0002] With the rapid development of aerospace technology, the complex application environment, the improvement of key performance and safety factor all put forward more stringent requirements on the high temperature resistant thermal structural materials of aircraft. Carbon fiber reinforced carbon composites have a series of advantages such as low density, small thermal expansion coefficient, high specific strength, high specific modulus, excellent thermal shock resistance and ablation resistance, and are currently one of the few that can maintain high mechanical properties above 2000 °C. It is one of the best materials, but its oxidation resistance is poor, and it starts to oxidize in an oxidizing environment above 450°C, and its mechanical ...

Claims

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Application Information

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IPC IPC(8): C04B35/66C04B35/83C04B35/80C04B35/58C04B35/565
CPCC04B35/565C04B35/58078C04B35/66C04B35/806C04B35/83C04B2235/3804C04B2235/5248C04B2235/5256C04B2235/614C04B2235/616C04B2235/96
Inventor 罗瑞盈王潇安康
Owner BEIHANG UNIV
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