A kind of sandwich structure c/c-sic composite material and preparation method thereof

A composite material and sandwich technology, which is applied in the field of sandwich structure C/C-SiC composite material and its preparation, can solve the problems of long cycle, high preparation cost, and limited popularization and application, and achieve short cycle, lower material density, and low energy consumption Effect

Active Publication Date: 2020-08-04
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the preparation cost of this process is high and the cycle is long, generally 1000-1500 hours, which limits the popularization and application of this material

Method used

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  • A kind of sandwich structure c/c-sic composite material and preparation method thereof
  • A kind of sandwich structure c/c-sic composite material and preparation method thereof
  • A kind of sandwich structure c/c-sic composite material and preparation method thereof

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Effect test

preparation example Construction

[0043] (2) Preparation of interface layer

[0044] Pyrolytic carbon is used as the carbon fiber interface layer. The introduction of pyrolytic carbon not only makes the material meet the debonding conditions, but also can regulate the residual thermal stress and reduce the frictional resistance caused by the roughness of the debonding surface, thus affecting the debonding. The size of the sliding resistance on the surface affects the contribution of fiber pulling out to the toughening effect.

[0045] The pyrolytic carbon interface layer was prepared by the ICVI process (such as figure 2 ). The raw material gas is Ar or N 2 For diluting gas, the flow rate is 0.05~0.5m 3 / h; liquefied natural gas (or methane, propane) is carbon source gas, the flow rate is 0.01~0.5m 3 / h; the deposition temperature is 700-1100° C., the deposition time is 3-10 h, and the thickness of the finally prepared pyrolytic carbon interface layer is 0.3-2 um.

[0046] (3) Preparation of intermediate...

Embodiment 1

[0056] Taking 380×80×9mm as an example, the density is 0.5g / cm 3 2D needle felt; Pyrolytic carbon interface layer prepared by ICVI process, temperature 900°C, argon flow rate 0.2m 3 / h, propane 0.15m 3 / h, the deposition time is 5 hours; the C / C composite material with dense center and porous sides is prepared by E-CVI process, the temperature is 700-1000°C, the flow ratio of argon:propane is 2:1, and the deposition time is 5 hours; E-CVI process to deposit SiC substrate, pass hydrogen, argon and trichloromethylsilane into the E-CVI furnace, the volume ratio is 5:5:1, the temperature is 700-1000°C, and the deposition is 15 hours to obtain the required sandwich structure Composite material; after CNC machining and forming, ultrasonic cleaning; CVD coating, temperature 1200 ° C, hydrogen, argon and trichloromethylsilane, volume ratio 5:5:1, time 30 hours, the final density of the material is 1.95g / cm 3 , The total material preparation cycle is 55 hours. Figure 5 Backscatt...

Embodiment 2

[0058] Take 380×80×30mm as an example, the density is 0.5g / cm 3 2D needle felt; Pyrolytic carbon interface layer prepared by ICVI process, temperature 900°C, argon flow rate 0.2m 3 / h, propane 0.15m 3 / h, the deposition time is 5 hours; the C / C gradient material is prepared by E-CVI process, the temperature is 700-1000 °C, the flow ratio of argon:propane is 2:1, and the deposition time is 15 hours; the SiC substrate is deposited by E-CVI process , put hydrogen, argon and trichloromethylsilane into the E-CVI furnace, the volume ratio is 5:5:1, the temperature is 700-1000°C, and the composite material with the required sandwich structure is obtained after deposition for 25 hours; CNC machining is adopted After forming, ultrasonic cleaning; CVD coating, temperature 1200 ℃, hydrogen, argon and trichloromethylsilane, volume ratio 5:5:1, cycle 30 hours, final density of material 1.90g / cm 3 , The total material preparation cycle is less than 75 hours.

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Abstract

The invention discloses a C / C-SiC composite material of a sandwich structure and a preparation method thereof, belonging to the technical field of carbon fiber reinforced ceramic-based composite materials. The composite material is specifically as follows: a novel sandwich structure composite material of which the middle is provided with high-density C / C and two sides are respectively provided with C / C-SiC and C / SiC in symmetrical distribution is designed. The invention further discloses a novel process for rapidly preparing the C / C-SiC composite material of the sandwich structure. The material is low in density and excellent in oxidation resistance and high-temperature mechanical property. The process has the characteristics of short preparation cycle, low cost, low energy consumption andthe like. According to the implementation, the application range of the C / C-SiC composite material in an aerospace system can be widened.

Description

Technical field: [0001] The invention relates to the technical field of carbon fiber reinforced ceramic matrix composite materials, in particular to a sandwich structure C / C-SiC composite material and a preparation method thereof, which can expand the application of the C / C-SiC composite material in aerospace systems. Background technique: [0002] As an excellent thermal structural composite material, C / C-SiC composite material has the following characteristics: (1) Strong designability: the strength, modulus, and thermophysical properties of the material are designable; (2) High temperature mechanical properties Excellent: maintains high strength at 1700°C; (3) has strong oxidation resistance: it can be used for a long time in an oxidizing atmosphere at 1650°C; (4) low density: dense C / C-SiC composite material density is at 1.8-2.1g / cm 3 (5) High hardness, high fracture toughness, low thermal expansion coefficient, excellent thermal shock resistance, etc. At present, C / C...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/83C04B35/84C04B35/80C04B41/87B32B37/00
CPCB32B37/0076C04B35/806C04B35/83C04B41/009C04B41/5059C04B41/87C04B2235/612C04B2235/77C04B2235/96C04B41/4531
Inventor 汤素芳庞生洋胡成龙杨鸷
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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