期刊文献+

先驱体浸渗裂解法制备C/C-SiC复合材料的烧蚀性能(英文) 被引量:6

ABLATION PROPERTIES OF C/C-SiC COMPOSITES BY PRECURSOR INFILTRATION AND PYROLYSIS PROCESS
下载PDF
导出
摘要 用先驱体浸渗裂解法制备了碳纤维增强碳(carbon fiber reinforced carbon,C/C)-SiC复合材料,用H2-O2火焰法检测其烧蚀性能。结果表明:C/C-SiC复合材料的烧蚀率随复合材料中的Si含量的增加而呈下降趋势;经过5次浸渍,C/C-SiC复合材料的密度从1.46 g/cm3增加到1.75 g/cm3,Si含量从5.06%增加到13.8%,线烧蚀率和质量烧蚀率分别下降474%和34.5%。密度为1.75 g/cm3的C/C–SiC复合材料,其线烧蚀率和质量烧蚀率分别为2.22μm/s和1.289 mg/s,其线烧蚀率和质量烧蚀率分别为密度1.78 g/cm3的C/C复合材料的21.7%和78.6%。基体中SiC的引入明显提高了C/C复合材料的抗氧化烧蚀性能。 Carbon fiber reinforced carbon (C/C) -SiC composites were prepared by the precursor infiltration and pyrolysis process, and the ablation properties of the C/C-SiC composites were investigated by the H2-O2 torch flame. The results indicate that the ablation rate of C/C-SiC composites decrease with the increase of Si contents. After infiltration is carried for 5 times, the density of C/C-SiC composites increases from 1.46 g/cm3 to 1.75 g/cm3 and the Si content increases from 5.06% to 13.8%. Meanwhile, the linear ablation rate and mass ablation rate of C/C-SiC specimens decrease by 574% and 134.5%, respectively. The linear ablation rate and mass ablation rate of the C/C-SiC composite with a density of 1.75 g/cm3 are 2.22/.trrds and 1.289mg/s, only 21.7% and 78.6% of those of the C/C composite with a density of 1.78 g/cm3, respectively. The introduction of SiC in the matrix greatly enhances the anti-oxidative ablation property of the C/C composite.
出处 《硅酸盐学报》 EI CAS CSCD 北大核心 2008年第7期973-977,984,共6页 Journal of The Chinese Ceramic Society
关键词 碳/碳-碳化硅复合材料 烧蚀 先驱体浸渗裂解法 抗氧化 carbon/carbon-silicon carbide composite ablation precursor infiltration and pyrolysis process anti-oxidation
  • 相关文献

参考文献7

二级参考文献73

  • 1李建军,陈来,孙晋良,周春节,张家宝,任慕苏.聚碳硅烷/二乙烯基苯与聚硅烷/二乙烯基苯的交联与裂解[J].上海大学学报(自然科学版),2004,10(5):479-483. 被引量:4
  • 2苏波,刘军,陈朝辉.聚碳硅烷/过氧化二异丙苯的交联[J].高分子材料科学与工程,1994,10(1):38-43. 被引量:5
  • 3邓景屹,刘文川,魏永良,王作明,高守山.炭纤维增强C—SiC梯度基复合材料的结构与性能[J].炭素,1996(1):18-23. 被引量:3
  • 4胡海峰.国防科技大学学报,1997,19(6):113-117.
  • 5Hlratzer A,Pfeiffer H.All-ceramic body flaps for re-entry spacecraft[J].SAMPE,2002,38(4):22-29.
  • 6Papenburg U,Beyer S,Laube H.Advanced ceramic matrix composites for space propulsion systems[R].AIAA97-3391.
  • 7Beyer S,Knabe H.Development and testing of C/SiC components for liquid rocket propulsion applications [R].AIAA99-2896.
  • 8Felix F,William F,Nancy R.An innovative thermal management system for a mach 4 to mach 8 hypersonic scramjet engine[R].AIAA98-3734.
  • 9Siebenhaar A,Johnson R W.Aero jet storable fuel scramjet flow path concepts:phase I program overview [R].AIAA99-4923.
  • 10XU Y D,ZHANG L T.Three-dimensional carbon / silicon carbide composites prepared by chemical vapor infiltration [J].J Am Ceram Soc,1997,80 (7):1897-1900.

共引文献76

同被引文献107

引证文献6

二级引证文献78

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部