Carbon-silicon carbide base composite material toughened by carbon fiber and its preparation method

A composite material, silicon carbide-based technology, applied in chemical instruments and methods, layered products, ceramic layered products, etc., can solve the problem that the thermal expansion matching of carbon fiber and silicon carbide matrix is ​​not ideal, 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, reduced elastic modulus, and good thermal expansion matching

Inactive Publication Date: 2006-11-29
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 impregnate the carbon fiber braid by vacuum-pressure method;

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

[0017] (3) Place 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 a vacuum of 0.5 h, 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) configuration mass ratio is the polycarbosilane / vinylbenzene solution of 1: 0.4;

[0019] (5) Place the carb...

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 impregnate the carbon fiber braid by vacuum-pressure method;

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

[0024] (3) Place 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 a vacuum of 0.5 h, 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 polycarbosilane / vinylbenzen...

Embodiment 3

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

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

[0033] (3) Place 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 vacuuming 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) configuration mass ratio is the polycarbosilane / vinylbenzene solution of 1: 0.4; ...

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PUM

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Abstract

A carbon fiber toughened carbon-silicon carbide based composition with high thermal expansion match performance, low-temp antioxidizing performance, toughness and purity features that its reinforcing phase is carbon fiber, its basic body phase is the alternatively laminated 2-5 carbon-silicon carbide layers, and its external layer is silicon carbide for high antioxidizing performance. Its preparing process is sequential impregnation and thermodecomposing of boronphenolic aldehyde and polycarbonsilane.

Description

technical field [0001] The invention relates to a carbon-silicon carbide based composite material and a preparation method thereof, in particular to a carbon fiber toughened carbon-silicon carbide based composite material and a preparation method thereof. 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 ...

Claims

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Application Information

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