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首页> 外文会议>55th International Astronautical Congress 2004 vol.3 >HIGH PERFORMANCE C/SIC COMPOSITES WITH MULTILAYERED INTERPHASE USED FOR SPACE ROCKET
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HIGH PERFORMANCE C/SIC COMPOSITES WITH MULTILAYERED INTERPHASE USED FOR SPACE ROCKET

机译：用于航天火箭的具有多层界面的高性能C / SIC复合材料

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摘要

Carbon fibers reinforced silicon carbide composite (C/SiC) offers excellent high temperature. However, high thermal conductivity precludes the C/SiC composite application in insulating structural components. A high strength, high roughness, and low thermal conductivity 2.5D C/SiC composite for space rocket component was manufactured by CVI+PIP combined process. In PIP process 10wt% SiO_2 nano-powders were filled in impregnant as low thermal conductivity filler. Before matrix densification, 2.5D carbon fibrous preform with the fiber volume content of 45% was coated with C/SiC/C multilayered interphase. SEM microstructure analysis indicated that there were many pulled-out fibers in cross-section of fracture composite specimen. The carbon fibers in the composite with C/SiC/C multilayered coating were not being eroded by SiO_2 fillers. The C/SiC composites exhibited excellent mechanical and insulation properties at room temperature with fracture toughness of 15.2MPa-m~(1/2), flexural strength of 543MPa, and thermal conductivity of 3.45W/m-K. The high temperature (1300· ) properties of this material were also good with flexural strength of 527MPa.
机译：碳纤维增强的碳化硅复合材料（C / SiC）具有出色的高温。然而，高导热率排除了C / SiC复合材料在绝缘结构部件中的应用。采用CVI + PIP复合工艺制造了一种高强度，高粗糙度，低导热率的2.5D C / SiC复合材料。在PIP工艺中，将10wt％的SiO_2纳米粉体填充为低导热率的浸渍剂。在基体致密化之前，将纤维体积含量为45％的2.5D碳纤维预成型坯涂以C / SiC / C多层界面。扫描电镜（SEM）的显微结构分析表明，复合材料断裂断面上有许多拉出的纤维。具有C / SiC / C多层涂层的复合材料中的碳纤维不会被SiO_2填料侵蚀。 C / SiC复合材料在室温下具有优异的机械和绝缘性能，断裂韧性为15.2MPa-m〜（1/2），弯曲强度为543MPa，导热系数为3.45W / m-K。该材料的高温（1300·）性能也很好，弯曲强度为527MPa。

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