High performance C/SIC composites with multilayered interphase used for space rocket

Liansheng Yan; Xiaohu Zhang; Hejun Li; Hong Cui

High performance C/SIC composites with multilayered interphase used for space rocket

Liansheng Yan, Xiaohu Zhang, Hejun Li, Hong Cui

School of Materials Sience and Engineering

Research output: Contribution to conference › Paper › peer-review

Abstract

Carbon fibers reinforced silicon carbide composite (C/SiC) offers excellent high temperature. However, high thermal conductivity precludes the C/SiC composite application in insulating structural components. A high strength, high roughness, and low thermal conductivity 2.5D C/SiC composite for space rocket component was manufactured by CVI+PIP combined process. In PIP process 10wt% SiO₂ nano-powders were filled in impregnant as low thermal conductivity filler. Before matrix densification, 2.5D carbon fibrous preform with the fiber volume content of 45% was coated with C/SiC/C multilayered interphase. SEM microstructure analysis indicated that there were many pulled-out fibers in cross-section of fracture composite specimen. The carbon fibers in the composite with C/SiC/C multilayered coating were not being eroded by SiO₂ fillers. The C/SiC composites exhibited excellent mechanical and insulation properties at room temperature with fracture toughness of 15.2MPa·m^1/2, flexural strength of 543MPa, and thermal conductivity of 3.45W/m·K. The high temperature (1300) properties of this material were also good with flexural strength of 527MPa.

Original language	English
Pages	1907-1911
Number of pages	5
State	Published - 2004
Event	International Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, Canada Duration: 4 Oct 2004 → 8 Oct 2004

Conference

Conference	International Astronautical Federation - 55th International Astronautical Congress 2004
Country/Territory	Canada
City	Vancouver
Period	4/10/04 → 8/10/04

Cite this

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title = "High performance C/SIC composites with multilayered interphase used for space rocket",

abstract = "Carbon fibers reinforced silicon carbide composite (C/SiC) offers excellent high temperature. However, high thermal conductivity precludes the C/SiC composite application in insulating structural components. A high strength, high roughness, and low thermal conductivity 2.5D C/SiC composite for space rocket component was manufactured by CVI+PIP combined process. In PIP process 10wt% SiO2 nano-powders were filled in impregnant as low thermal conductivity filler. Before matrix densification, 2.5D carbon fibrous preform with the fiber volume content of 45% was coated with C/SiC/C multilayered interphase. SEM microstructure analysis indicated that there were many pulled-out fibers in cross-section of fracture composite specimen. The carbon fibers in the composite with C/SiC/C multilayered coating were not being eroded by SiO2 fillers. The C/SiC composites exhibited excellent mechanical and insulation properties at room temperature with fracture toughness of 15.2MPa·m1/2, flexural strength of 543MPa, and thermal conductivity of 3.45W/m·K. The high temperature (1300) properties of this material were also good with flexural strength of 527MPa.",

author = "Liansheng Yan and Xiaohu Zhang and Hejun Li and Hong Cui",

year = "2004",

language = "英语",

pages = "1907--1911",

note = "International Astronautical Federation - 55th International Astronautical Congress 2004 ; Conference date: 04-10-2004 Through 08-10-2004",

}

TY - CONF

T1 - High performance C/SIC composites with multilayered interphase used for space rocket

AU - Yan, Liansheng

AU - Zhang, Xiaohu

AU - Li, Hejun

AU - Cui, Hong

PY - 2004

Y1 - 2004

N2 - Carbon fibers reinforced silicon carbide composite (C/SiC) offers excellent high temperature. However, high thermal conductivity precludes the C/SiC composite application in insulating structural components. A high strength, high roughness, and low thermal conductivity 2.5D C/SiC composite for space rocket component was manufactured by CVI+PIP combined process. In PIP process 10wt% SiO2 nano-powders were filled in impregnant as low thermal conductivity filler. Before matrix densification, 2.5D carbon fibrous preform with the fiber volume content of 45% was coated with C/SiC/C multilayered interphase. SEM microstructure analysis indicated that there were many pulled-out fibers in cross-section of fracture composite specimen. The carbon fibers in the composite with C/SiC/C multilayered coating were not being eroded by SiO2 fillers. The C/SiC composites exhibited excellent mechanical and insulation properties at room temperature with fracture toughness of 15.2MPa·m1/2, flexural strength of 543MPa, and thermal conductivity of 3.45W/m·K. The high temperature (1300) properties of this material were also good with flexural strength of 527MPa.

AB - Carbon fibers reinforced silicon carbide composite (C/SiC) offers excellent high temperature. However, high thermal conductivity precludes the C/SiC composite application in insulating structural components. A high strength, high roughness, and low thermal conductivity 2.5D C/SiC composite for space rocket component was manufactured by CVI+PIP combined process. In PIP process 10wt% SiO2 nano-powders were filled in impregnant as low thermal conductivity filler. Before matrix densification, 2.5D carbon fibrous preform with the fiber volume content of 45% was coated with C/SiC/C multilayered interphase. SEM microstructure analysis indicated that there were many pulled-out fibers in cross-section of fracture composite specimen. The carbon fibers in the composite with C/SiC/C multilayered coating were not being eroded by SiO2 fillers. The C/SiC composites exhibited excellent mechanical and insulation properties at room temperature with fracture toughness of 15.2MPa·m1/2, flexural strength of 543MPa, and thermal conductivity of 3.45W/m·K. The high temperature (1300) properties of this material were also good with flexural strength of 527MPa.

UR - http://www.scopus.com/inward/record.url?scp=34249003061&partnerID=8YFLogxK

M3 - 论文

AN - SCOPUS:34249003061

SP - 1907

EP - 1911

T2 - International Astronautical Federation - 55th International Astronautical Congress 2004

Y2 - 4 October 2004 through 8 October 2004

ER -

High performance C/SIC composites with multilayered interphase used for space rocket

Abstract

Conference

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