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Preparation method of carbon-silicon carbide base composite material toughened by carbon fiber

A technology of silicon carbide-based and composite materials, which is applied in chemical instruments and methods, layered products, ceramic layered products, etc., can solve the problem of unsatisfactory thermal expansion matching between carbon fiber and silicon carbide matrix, affecting the mechanical and thermal properties of composite materials, Restricting the development of composite materials and other issues, to achieve the effect of convenient structural design and optimization, lower elastic modulus, and good thermal expansion matching

Inactive Publication Date: 2009-08-26
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage of carbon fiber reinforced silicon carbide composite materials is that the thermal expansion matching between carbon fiber and silicon carbide matrix is ​​not ideal, and there are many low-temperature crack defects, which affect the mechanical and thermal properties of composite materials and restrict the development of composite materials.
The disadvantage of the precursor conversion method is that multiple impregnations are required, and the high temperature cracking of polycarbosilane in the first cycle will cause chemical damage to the fiber, which is not conducive to the improvement of the performance of the composite material

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0015] (1). Soak the continuous carbon fiber braid in acetone for about 30 minutes, remove the carbon fiber surface treatment agent epoxy resin, dry at low temperature, and remove the acetone solvent. Then vacuum-pressurization method is used to impregnate the carbon fiber braid;

[0016] (2). 100g boron phenolic aldehyde and 100g alcohol miscibility, be mixed with organic precursor solution;

[0017] (3). Put the carbon fiber braid in a pre-prepared mold, fix the braid on the mold with cotton thread, take it out after impregnating for a period of time, transfer the sample to an autoclave, heat up to 50°C, and maintain the vacuum 0.5h, then add 6MPa air pressure, keep it for 1h, then raise the temperature to 180°C for pre-curing for 2h, and finally raise the temperature to 230°C for post-curing, and then put the sample in a pit furnace at 1000°C, N 2 Medium cracking 6h;

[0018] (4). Configure a polycarbosilane / vinylbenzene solution with a mass ratio of 1:0.4;

[0019] (5)....

Embodiment 2

[0022] (1). Soak the continuous carbon fiber braid in acetone for about 30 minutes, remove the carbon fiber surface treatment agent epoxy resin, dry at low temperature, and remove the acetone solvent. Then vacuum-pressurization method is used to impregnate the carbon fiber braid;

[0023] (2). 100g boron phenolic aldehyde and 100g alcohol miscibility, be mixed with organic precursor solution;

[0024] (3). Put the carbon fiber braid in a pre-prepared mold, fix the braid on the mold with cotton thread, take it out after impregnating for a period of time, transfer the sample to an autoclave, heat up to 50°C, and maintain the vacuum 0.5h, then add 6MPa air pressure, keep it for 1h, then raise the temperature to 180°C for pre-curing for 2h, and finally raise the temperature to 230°C for post-curing, and then put the sample in a pit furnace at 1000°C, N 2 Medium cracking 6h;

[0025] (4). Carry out the process described in step (3) once again;

[0026] (5). Configure a polycarbo...

Embodiment 3

[0031] (1). Soak short-fiber-rolled carbon felt in acetone for about 30 minutes, remove carbon fiber surface treatment agent epoxy resin, dry at low temperature, and remove acetone solvent. Then impregnate the short-fiber rolled carbon felt by vacuum-pressure method;

[0032] (2). 100g boron phenolic aldehyde and 100g alcohol miscibility, be mixed with organic precursor solution;

[0033] (3). Put the short-fiber rolled carbon felt in a pre-prepared mold, fix the carbon felt on the mold with cotton thread, take it out after impregnating for a period of time, transfer the sample to an autoclave, and heat up to 50°C , keep the vacuum for 0.5h, then add 6MPa air pressure, keep it for 1h, then raise the temperature to 180°C for pre-curing for 2h, and finally raise the temperature to 230°C for post-curing, then put the sample in a pit furnace at 1000°C, N 2 Medium cracking 6h;

[0034] (4). Configure a polycarbosilane / vinylbenzene solution with a mass ratio of 1:0.4;

[0035] (5...

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PUM

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Abstract

A carbon fiber-toughened carbon-silicon carbide matrix composite material is characterized in that the reinforcing phase is carbon fiber, the matrix phase is formed by sequentially stacking 2 to 5 layers of carbon and silicon carbide, and the outermost layer is silicon carbide to ensure the strength of the composite material. Antioxidant properties. A method for preparing a carbon fiber toughened carbon-silicon carbide matrix composite material, characterized in that it is formed by sequentially impregnating and pyrolyzing boron phenolic aldehyde and polycarbosilane. The main advantages of the invention are: (1) the thermal expansion of the carbon fiber and the carbon-silicon carbide matrix is ​​well matched, the low-temperature crack defects of the composite material are significantly reduced, and the low-temperature oxidation resistance is improved; (2) the elastic modulus of the composite material is reduced, and the fracture toughness of the composite material is improved; (3) The preparation method has a short period and low cost, and is convenient for structural design and optimization of the matrix of the composite material; (4) The prepared carbon fiber toughened carbon-silicon carbide matrix composite material has high purity. (5) The carbon fiber can be a continuous carbon fiber braid or a short-fiber rolled carbon felt; (6) The matrix of the composite material is composed of carbon and silicon carbide, and its density is lower than that of carbon fiber toughened silicon carbide.

Description

technical field [0001] The invention relates to a method for preparing a carbon-silicon carbide based composite material, in particular to a method for preparing a carbon fiber toughened carbon-silicon carbide based composite material. Background technique [0002] With the development of new engines and the development of new concept space vehicles, higher requirements are put forward for high temperature structural materials. Fiber-reinforced ceramic matrix composites have excellent properties such as high strength, high toughness, high temperature resistance, good corrosion resistance and low density at high temperatures, and have broad application prospects in the fields of strategic weapons and space technology. In recent years, more and more By the attention of material workers. [0003] SiC ceramics have good high-temperature strength, high-temperature stability, and high-temperature oxidation resistance, but due to the bonding characteristics of its molecular struct...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/83C04B35/52C04B35/565B32B18/00
Inventor 陈照峰严波
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS