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反应熔渗工艺制备的C/C-SiC复合材料烧蚀性能及构件研制 被引量:2

Component development and ablation properties of C/C-SiC composites prepared with RMI process
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摘要 采用反应熔渗工艺(RMI)快速制备了不同碳化硅含量的C/C-SiC复合材料,通过氧-乙炔烧蚀试验,测试了材料的烧蚀性能。利用SEM/EDS表征了复合材料烧蚀后的表面形貌和成分,分析了碳化硅含量对复合材料烧蚀性能的影响。结果表明,随着基体中碳化硅含量的提高,烧蚀过程中生成的二氧化硅保护膜更加致密,导致C/C-SiC复合材料的烧蚀率逐渐降低。在此基础上,利用优化工艺制备了密度均匀的大尺寸C/C-SiC构件,经过地面热试车考核,构件接近零烧蚀,满足发动机热试车的应用。 Carbon fiber reinforced carbon and silicon carbide matrix(C/C-SiC)composites with different SiC contents were prepared by reaction melt infiltration(RMI)process.The ablative properties of the composites were tested by oxyacetylene ablation technique.The microstructure and ablative behavior of the C/C-SiC composites have been investigated.With the increase of the SiC content in the C/C-SiC composites,the SiO 2 produced during the ablative process becomes dense,and then the ablative ratio of the composites decreases.On the basis of this fact,large size C/C-SiC components with uniform density were prepared by a optimizated process.After the ground thermal testing,the components were closed to zero ablation and met the application of the motor thermal testing.
作者 康文杰 薛如月 赵大明 张永辉 程皓 彭志刚 苏君明 KANG Wenjie;XUE Ruyue;ZHAO Daming;ZHANG Yonghui;CHENG Hao;PENG Zhigang;SU Junming(Xi’an Chaoma Technology Co.,Ltd,Xi’an 710025,China;Xi’an Xiangyang Aerospace Materials Co.,Ltd,Xi’an 710025,China)
出处 《固体火箭技术》 EI CAS CSCD 北大核心 2019年第4期519-522,552,共5页 Journal of Solid Rocket Technology
关键词 反应熔渗法 碳化硅含量 烧蚀性能 热试车考核 reaction melt infiltration SiC content ablation property thermal testing
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