摘要
分别使用固体和液体火箭发动机实验系统对C/SiC陶瓷基复合材料的烧蚀性能进行了考核实验,主要研究了烧蚀时间、粒子和温度对材料烧蚀性能的影响。实验结果表明:随着烧蚀时间加长,材料烧蚀性能有明显下降趋势;温度高于2 973 K时,烧蚀明显加剧,且温度越高烧蚀越严重;强氧化燃气环境下,大量的H2O加剧了材料的热化学烧蚀。
Sections 1 and 2 of the full paper explain our experimental study. Their core consists of： （ 1 ） Fig. 1 shows the sketch of our experimental setup of oxygen/alcohol gas generator; （2）subsection 1.2 is entitled ＂experimental parameters＂ ; （3）Table 1 presents the results of 3D C/SiC ablation experiments for different lengths of ablation time; the analysis of these results shows that the ablative performance decays with longer ablation time; this analysis also shows that the ablation becomes acute when the temperature is higher than 2973K, and the higher the temperature, the more significant the ablation is; （4） Tables 2 and 3 present the mass contents of main gas compo- nents determined experimentally for solid rocket motor and liquid rocket engine respectively; our analysis of these results shows that particle, such as AI90, in Table 2, does not olav an imnortant role in ablation.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2011年第4期598-602,共5页
Journal of Northwestern Polytechnical University
关键词
火箭发动机
烧蚀
C/SIC复合材料
ablation
rocket engines
solid propellants
liquid propellants
composite materials
C/SiC
