摘要
研究了三种增强体结构,即炭布叠层增强骨架(P型结构)、原位针刺骨架(N型结构)、整体编织骨架(W型结构),以及增强结构对炭/炭复合材料(C/C)出口锥热性能的影响。结果表明,三种增强结构C/C材料比热相近,随温度升高而增加;增强结构的各向异性对材料导热率影响明显,X-Y向的导热率均大于Z向,P-C/C面内和径向导热率相差10倍以上;N-C/C在两个方向导热率差别最小,各向异性度明显降低;W-C/C在两个方向导热率差别也较明显,径向导热率比P-C/C高,但低于N-C/C;热膨胀系数随增强结构不同呈显著各向异性,Z向和XY向热膨胀系数的比值(ZCTE/XYCTE)可表征C/C材料热膨胀性能的各向异性程度,P-C/C两个方向差异最大,W-C/C次之,N-C/C最小;随测试温度升高,N-C/C、W-C/C的ZCTE/XYCTE比值逐渐变小。
Three kind of carbon fiber preforms,carbon cloth ply preform(P preform),needled caborn cloth preform(N preform)and carbon fiber weaving preform(W preform),are investigated for three kind of carbon-carbon composites(C/C),P-C/C,N-C/C,W-C/C,which are used for nozzle exit cone,as well as the influence of reinforcement structure on thermal properties of three C/C are also studied.It is found that thermal capability of the three C/C are close and all increase with increasing testing temperature.The anisotropy deg...
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2007年第5期1358-1361,1414,共5页
Journal of Astronautics
关键词
炭/炭材料
出口锥
增强体结构
热性能
各向异性
Carbon-carbon composites
Exit cone
Reinforcement structure
Thermal property
Anisotropy
