摘要
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.
源语言 | 英语 |
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页(从-至) | 393-396+411 |
期刊 | Guti Huojian Jishu/Journal of Solid Rocket Technology |
卷 | 31 |
期 | 4 |
出版状态 | 已出版 - 8月 2008 |