Preparation and property characterization of C/SiC composite thruster

Lian Sheng Yan; Ke Zhi Li; He Jun Li

Preparation and property characterization of C/SiC composite thruster

Lian Sheng Yan, Ke Zhi Li, He Jun Li

School of Materials Sience and Engineering

Northwestern Polytechnical University Xian

Research output: Contribution to journal › Article › peer-review

1 Scopus citations

Abstract

Continuous carbon fiber reinforced silicon carbide matrix composite thrusters were prepared by using" chemical vapor infiltration+precursor impregnation pyrolysis" (CVI+PIP) hybrid process. The mechanical properties, gas tightness and microstructure of 3D C/SiC composites were comprehensively investigated through attitude control and orbit control rocket motor environmental test. The results show that CVI+PIP hybrid process can not only shorten process cycle, but also improve composite properties. The density of C/SiC composite can reach 2.1 g/cm³. The flexural strength and fracture toughness (KIC) of the composite at room temperature are 520 MPa and 17.9 MPa·m^1/2 respectively. The fracture damage behavior of the composite presents typical toughness mode. High-temperature gas tightness, anti-oxidation and ablation properties of the C/SiC composite thruster are verified through bipropellant liquid rocket motor test.

Original language	English
Pages (from-to)	393-396+411
Journal	Guti Huojian Jishu/Journal of Solid Rocket Technology
Volume	31
Issue number	4
State	Published - Aug 2008

Keywords

"CVI+PIP" process
Carbon/silicon carbide composite
Thruster

Cite this

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title = "Preparation and property characterization of C/SiC composite thruster",

abstract = "Continuous carbon fiber reinforced silicon carbide matrix composite thrusters were prepared by using{"} chemical vapor infiltration+precursor impregnation pyrolysis{"} (CVI+PIP) hybrid process. The mechanical properties, gas tightness and microstructure of 3D C/SiC composites were comprehensively investigated through attitude control and orbit control rocket motor environmental test. The results show that CVI+PIP hybrid process can not only shorten process cycle, but also improve composite properties. The density of C/SiC composite can reach 2.1 g/cm3. The flexural strength and fracture toughness (KIC) of the composite at room temperature are 520 MPa and 17.9 MPa·m1/2 respectively. The fracture damage behavior of the composite presents typical toughness mode. High-temperature gas tightness, anti-oxidation and ablation properties of the C/SiC composite thruster are verified through bipropellant liquid rocket motor test.",

keywords = "{"}CVI+PIP{"} process, Carbon/silicon carbide composite, Thruster",

author = "Yan, {Lian Sheng} and Li, {Ke Zhi} and Li, {He Jun}",

year = "2008",

month = aug,

language = "英语",

volume = "31",

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journal = "Guti Huojian Jishu/Journal of Solid Rocket Technology",

issn = "1006-2793",

publisher = "Journal of Solid Rocket Technology",

number = "4",

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T1 - Preparation and property characterization of C/SiC composite thruster

AU - Yan, Lian Sheng

AU - Li, Ke Zhi

AU - Li, He Jun

PY - 2008/8

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N2 - Continuous carbon fiber reinforced silicon carbide matrix composite thrusters were prepared by using" chemical vapor infiltration+precursor impregnation pyrolysis" (CVI+PIP) hybrid process. The mechanical properties, gas tightness and microstructure of 3D C/SiC composites were comprehensively investigated through attitude control and orbit control rocket motor environmental test. The results show that CVI+PIP hybrid process can not only shorten process cycle, but also improve composite properties. The density of C/SiC composite can reach 2.1 g/cm3. The flexural strength and fracture toughness (KIC) of the composite at room temperature are 520 MPa and 17.9 MPa·m1/2 respectively. The fracture damage behavior of the composite presents typical toughness mode. High-temperature gas tightness, anti-oxidation and ablation properties of the C/SiC composite thruster are verified through bipropellant liquid rocket motor test.

AB - Continuous carbon fiber reinforced silicon carbide matrix composite thrusters were prepared by using" chemical vapor infiltration+precursor impregnation pyrolysis" (CVI+PIP) hybrid process. The mechanical properties, gas tightness and microstructure of 3D C/SiC composites were comprehensively investigated through attitude control and orbit control rocket motor environmental test. The results show that CVI+PIP hybrid process can not only shorten process cycle, but also improve composite properties. The density of C/SiC composite can reach 2.1 g/cm3. The flexural strength and fracture toughness (KIC) of the composite at room temperature are 520 MPa and 17.9 MPa·m1/2 respectively. The fracture damage behavior of the composite presents typical toughness mode. High-temperature gas tightness, anti-oxidation and ablation properties of the C/SiC composite thruster are verified through bipropellant liquid rocket motor test.

KW - "CVI+PIP" process

KW - Carbon/silicon carbide composite

KW - Thruster

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M3 - 文章

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JO - Guti Huojian Jishu/Journal of Solid Rocket Technology

JF - Guti Huojian Jishu/Journal of Solid Rocket Technology

IS - 4

ER -

Preparation and property characterization of C/SiC composite thruster

Abstract

Keywords

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