航空材料学报2017，Vol.37Issue(1)：80-85,6.DOI:10.11868/j.issn.1005-5053.2015.000214
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
摘要
Abstract
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 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-1 after 200 s ablation. The C/C-SiC component have excellent integral bear-ing performance with the hydraulic bursting pressure of 6. 5 MPa, and the high temperature combination property of the C/C-SiC com-posite nozzle inner is verified through motor hot firing of solid propellant ramjet.关键词
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Key words
C/C-SiC composites/solid propellant ramjet/nozzle inner/anti-ablative performance/motor hot firing分类
通用工业技术引用本文复制引用
王玲玲,嵇阿琳,高亚奇,崔红,闫联生,庞菲..固体冲压发动机喷管用C/C-SiC复合材料[J].航空材料学报,2017,37(1):80-85,6.基金项目
国防重大基础科研项目(c0320110006) （c0320110006）
