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Ceramic-based composite material and preparation method and application thereof

A composite material and ceramic-based technology, which is applied in the field of ceramic-based composite materials and its preparation, can solve the problems of mechanical and anti-oxidation ablation performance decline, rapid oxidation, etc., and achieve the effect of improving oxidation resistance and ablation performance

Pending Publication Date: 2021-11-02
SHAOXING RES INST OF SHANGHAI UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, these materials have some shortcomings in terms of high temperature oxidation resistance and ablation. For example, C / C materials are rapidly oxidized in an aerobic environment at a temperature higher than 500 °C; SiC ceramic matrix composites have high thermal stability, but the temperature exceeds 1500 °C, the mechanical and anti-oxidative ablation properties decrease significantly due to the SiC crystal transformation

Method used

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  • Ceramic-based composite material and preparation method and application thereof
  • Ceramic-based composite material and preparation method and application thereof
  • Ceramic-based composite material and preparation method and application thereof

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preparation example Construction

[0028] The present invention also provides a method for preparing the ceramic matrix composite material described in the above technical solution, comprising the following steps:

[0029] impregnating the carbon fiber preform with a silicon boron carbon nitrogen impregnation solution to obtain an impregnated preform;

[0030] The impregnated preform is sequentially subjected to crosslinking, curing and pyrolysis to obtain a dense preform;

[0031] Chemical vapor deposition of silicon carbide on the surface of the dense preform forms a silicon carbide protective layer to obtain the ceramic matrix composite material.

[0032] In the invention, the carbon fiber preform is impregnated with a silicon-boron-carbon-nitrogen impregnating liquid to obtain an impregnated preform. In the present invention, the carbon fiber preform preferably includes a 3D woven carbon fiber preform, a 2.5D woven carbon fiber preform or a 2D woven carbon fiber preform, more preferably a 3D woven carbon f...

Embodiment 1

[0051] A cuboid 3D braided carbon fiber prefabricated body with a size of 60*80*12mm (with a porosity of 79%, and a fiber diameter of 6μm) was degummed at 1000°C for 2 hours under a nitrogen atmosphere, and then placed in a pressure reactor, poured Add polysilaborazane (produced by the Institute of Chemistry, Chinese Academy of Sciences) to cover the carbon fiber preform, and impregnate it under the condition of 1MPa for 4h; The cured preform was taken out and placed in a tube furnace, heated to 1000°C for 2.5 hours under a nitrogen atmosphere and pyrolyzed for 2.5 hours. After 7 cycles of impregnation-crosslinking curing-pyrolysis steps, it was treated at 1500°C for 2 hours to obtain a dense preform. ; The porosity of the dense preform is 7%, and the density is 2g / cm 3 ;

[0052] The dense preform is subjected to chemical vapor deposition to obtain a ceramic matrix composite material with a silicon carbide protective layer thickness of 1500nm; the gas source is a mixed gas w...

Embodiment 2

[0058] A cuboid 2.5-dimensional woven carbon fiber prefabricated body with a size of 60*80*12mm (with a porosity of 79%, and a fiber diameter of 6μm) was degummed at 1000°C for 2 hours in a nitrogen atmosphere, and then placed in a pressure reactor. Add polysilaborazane (produced by the Institute of Chemistry, Chinese Academy of Sciences) to cover the carbon fiber preform, and impregnate it under the condition of 2MPa for 4h; The cured preform was taken out and placed in a tube furnace, heated to 1000°C for 2.5 hours under a nitrogen atmosphere and pyrolyzed for 2.5 hours. After 7 cycles of impregnation-crosslinking curing-pyrolysis steps, it was treated at 1500°C for 2 hours to obtain a dense preform. ; The porosity of the dense preform is 6.2%, and the density is 1.95g / cm 3 ;

[0059] The dense preform is subjected to chemical vapor deposition to obtain a ceramic matrix composite material with a silicon carbide protective layer thickness of 750nm; the gas source is a mixed ...

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Abstract

The invention belongs to the technical field of ceramic-based composite materials, and particularly relates to a ceramic-based composite material and a preparation method and application thereof. The invention provides the ceramic-based composite material. The ceramic-based composite material comprises a fiber-reinforced silicon-boron-carbon-nitrogen matrix and a silicon carbide protective layer deposited on the surface of the fiber-reinforced silicon-boron-carbon-nitrogen matrix. The ceramic-based composite material provided by the invention comprises the silicon carbide protective layer deposited on the surface of the fiber-reinforced silicon-boron-carbon-nitrogen matrix, and silicon in the silicon carbide protective layer generates thicker silicon dioxide in a high-temperature aerobic environment to isolate external oxygen and protect the internal fiber-reinforced silicon-boron-carbon-nitrogen matrix; therefore, the oxidation resistance and the ablation resistance of the ceramic-based composite material under the high-temperature (3000K) condition are improved.

Description

technical field [0001] The invention belongs to the technical field of ceramic matrix composite materials, and in particular relates to a ceramic matrix composite material and its preparation method and application. Background technique [0002] With the development of aerospace technology and military combat concepts, the advantages of near-space hypersonic re-entry gliding vehicles have become increasingly prominent. In the high-speed re-entry stage of near-space hypersonic re-entry gliding vehicles, the ablation temperature of high-enthalpy and high-heat flow can reach 3000 ℃, the duration is about tens of seconds; in the near-space gliding maneuver flight for a long time, the aerodynamic heating is very serious, the surface temperature of the aircraft is about 1980 ℃, the time is as long as hundreds to thousands of seconds, and the oxidation problem is prominent. In order to maintain a high lift-to-drag ratio and a good aerodynamic shape, each part of its outer surface i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/87
CPCC04B41/87C04B41/5059C04B41/009C04B41/4531C04B41/0072
Inventor 李爱军康治伟李志伟魏子涵茅思佳刘瑶瑶贾林涛彭雨晴
Owner SHAOXING RES INST OF SHANGHAI UNIV
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