固体冲压发动机喷管用C/C-SiC复合材料OA北大核心CSCDCSTPCD
C/C-SiC Composites for Nozzle of Solid Propellant Ramjet
采用“化学气相渗透+先驱体浸渍裂解”( CVI+PIP)混合工艺制备固体冲压发动机用C/C-SiC复合材料喷管内层,综合考查复合材料的微观结构、弯曲性能和抗烧蚀性能以及固冲发动机C/C-SiC喷管内层水压和点火实验。结果表明：复合材料的弯曲强度达到197 MPa,且断裂破坏行为呈现典型的韧性模式；复合材料具有优异的抗氧化烧蚀性能,氧化烧蚀200 s后线烧蚀率仅为0.0063 mm·s-1；研制的C/C-SiC复合材料构件的水压爆破压强为6.5 M…查看全部>>
Carbon fiber reinforced carbon and silicon carbide matrix composites for nozzle inner of solid propellant ramjet were prepared by using the hybrid process of “chemical vapor infiltration + precursor impregnation pyrolysis ( CVI + PIP)”. The microstructure, flexural and anti-ablation properties of the C/C-SiC composites and hydraulic test and rocket motor hot firing test for nozzle inner of sol-id propellant ramjet were comprehensively investigated. The resul…查看全部>>
王玲玲;嵇阿琳;高亚奇;崔红;闫联生;庞菲
西安航天复合材料研究所，西安710025西安航天复合材料研究所，西安710025 高性能碳纤维制造及应用国家地方联合工程研究中心，西安710089西安航天复合材料研究所，西安710025 高性能碳纤维制造及应用国家地方联合工程研究中心，西安710089西安航天复合材料研究所，西安710025
C/C-SiC复合材料固体冲压发动机喷管内层抗烧蚀性能试车
C/C-SiC compositessolid propellant ramjetnozzle inneranti-ablative performancemotor hot firing
《航空材料学报》 2017 (1)
80-85,6
国防重大基础科研项目(c0320110006)
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