摘要
通过等离子烧蚀发动机、小型烧蚀发动机点火试验及微观结构观察,研究了由化学液相沉积制备的炭 /炭复合材料的烧蚀性能,分析了其烧蚀前后微观结构的变化,并探讨了其作为固体发动机喉衬、扩散段材料的烧蚀机理。结果表明,由化学液相沉积工艺制得的沉积炭结构的抗烧蚀性能优于炭纤维,其作为喉衬的线烧蚀率为 0. 008mm/s,证明该工艺是可行的。
Through the plasma erosion test, small erosion motor firing test and microstructural observation,the erosion properties of carbon/carbon composites prepared by the chemical liquid deposition were studied, the microstructural changes of carbon/carbon composites before and after ablation were analyzed,and the ablation mechanism of the composite used for motor throat and exit cone was discussed.The results show that the ablation-protection properties of structure of deposited carbon prepared by the chemical liquid deposition are better than those of carbon fiber,the linear erosion rate of the composite used for motor throat is 0.008mm/s,and the composite preparation process is feasible.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2005年第1期57-59,共3页
Journal of Solid Rocket Technology
