固体冲压发动机喷管用C/C-SiC复合材料

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 MPa,表明构件具有良好的整体承载能力;C/C-SiC复合材料喷管内层高温综合性能通过了固体冲压发动机点火实验考核。

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 solid propellant ramjet were comprehensively investigated. The results show that when the flexural strength of the composite reachs 197 MPa,the fracture damage behavior of the composites presents typical toughness mode. Also the composites has excellent anti-ablative property,i. e.,linear ablation rate is only 0. 0063 mm·s^-1after 200 s ablation. The C/C-SiC component have excellent integral bearing performance with the hydraulic bursting pressure of 6. 5 MPa,and the high temperature combination property of the C/C-SiC composite nozzle inner is verified through motor hot firing of solid propellant ramjet.