A kind of c/sic composite material preparation method

A composite material and resorcinol technology, which is applied in the field of C/SiC composite material preparation, can solve the problems of low reaction activity of matrix carbon and liquid-phase silicon, low densification speed, and potential safety hazards, so as to improve mechanical properties and Anti-ablation performance, improved porosity and pore uniformity, and good overall product performance

A composite material and resorcinol technology, which is applied in the field of C/SiC composite material preparation, can solve the problems of low reaction activity of matrix carbon and liquid-phase silicon, low densification speed, and potential safety hazards, so as to improve mechanical properties and Anti-ablation performance, improved porosity and pore uniformity, and good overall product performance

CN108892524BActive Publication Date: 2020-12-25AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0043] Use resorcinol, formaldehyde and water according to the mass ratio of 6:9:15 and mix evenly for use. Put the carbon fiber preform into a container containing the above solution, vacuum impregnate it, and keep it for 1 hour. After curing at 180°C, after natural cooling, the preform was taken out for high temperature cracking at 800°C, and the above impregnation-curing-cracking process was repeated 5 times, and finally the density of 1.30g / cm3 was prepared. 3 Low-density C / C porous body material. Embed the low-density C / C composite material into silicon powder, heat it to 1450°C for 30 minutes under vacuum, then raise it to 1700°C within 1 hour, and keep it for 60 minutes to prepare a C / SiC composite material with a density of 2.0 g / cm 3 , The bending strength is 260MPa.

Embodiment 2

[0045] Use resorcinol, formaldehyde, and water according to the mass ratio of 5:9:40, mix well and set aside. Put the carbon fiber preform into a container containing the above solution, vacuum impregnate it, and keep it for 1 hour. After being cured at 180°C, the preform was taken out for high temperature cracking at 800°C, and the above impregnation-curing-cracking process was repeated 7 times, and finally a density of 1.31g / cm3 was prepared. 3 Low-density C / C porous body material. Embed the low-density C / C composite material into silicon powder, heat it to 1450°C for 30 minutes under vacuum, then raise it to 1700°C within 1 hour, and keep it for 60 minutes to prepare a C / SiC composite material with a density of 2.1 g / cm 3 , The bending strength is 272MPa.

Embodiment 3

[0047] Use resorcinol, formaldehyde and water according to the mass ratio of 5:9:15 and mix evenly for use. Put the carbon fiber preform into a container containing the above solution, vacuum impregnate it, and keep it for 1 hour. After curing at 180°C, the preform was taken out and subjected to high temperature cracking at 800°C, and the above impregnation-curing-cracking process was repeated 6 times, and finally a density of 1.35g / cm3 was prepared. 3 Low-density C / C porous body material. Embed the low-density C / C composite material into silicon powder, heat it to 1450°C for 30 minutes under vacuum, then raise it to 1700°C within 1 hour, and keep it for 60 minutes to prepare a C / SiC composite material with a density of 2.3 g / cm 3 , The bending strength is 265MPa.

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Abstract

The invention provides a preparation method of a C / SiC composite material. The C / SiC composite material is prepared by preparing a porous C / C composite material by means of an infiltration method. Asa special high-activity porous body C / C is adopted to reactive infiltration, the mechanical property and the anti- ablation property of the material are improved. The preparation method can be also applied to rapid low-cost preparation of a ceramic-based composite material.

Description

technical field [0001] The invention relates to a method for preparing a C / SiC composite material, which belongs to the technical field of composite material preparation. Background technique [0002] Developed countries such as the United States, France, Germany, and Japan have carried out extensive research on the preparation technology and application of C / SiC composite materials in the past 30 years. At present, C / SiC composite materials have been used as heat-resistant materials in reusable spacecraft and rocket engine systems, such as fuselage flaps, nose cone caps, wing leading edges of the US X-38 aircraft, and French SNECMA's The nozzle diffuser section of the HM7 large rocket engine. In addition, C / SiC composite materials also have broad application prospects in rocket engine combustion chambers, space mirrors, turbine engines, armor plates, and braking materials for aircraft and racing cars. [0003] The main preparation processes of C / SiC composite materials in...

Claims

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Application Information

Patent Timeline
25 Dec 2020
Publication
CN108892524B
IPC
C04B35/80; C04B35/565; C04B35/622; C04B35/65; C04B35/83; C04B38/06; C04B35/84
CPC
C04B35/806; C04B35/573; C04B35/622; C04B35/65; C04B35/83; C04B38/067; C04B2235/77; C04B2235/96
Inventors
王鹏; 于新民