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RESIN IMPREGNATING METHOD TO MAKE MULTI-MATRIX ANTI-ABLATION C/C COMPOSITE

机译:树脂浸渍法制备多基体抗烧蚀C / C复合材料

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摘要

The thermal, chemical, and mechanical environments produced by solid rocket motor (SRM), which has the uncooled nozzle, introduced many material problems in the development of rocket nozzles. Especially the throat material must bear the high temperature, mechanical load, thermal shock, chemical corrosion, and together with the highly requirement of dimensional stability. The materials used as throat including refractory metals, ceramics, graphite and fiber-reinforced plastics and so on, meet the needs of the early stage SRM, but some of them have high density, some can't withstand thermal shock and some can be ablated easily, all of them lead to big inert mass, so as to restrict the progress of the nozzle efficiency. There are some literatures about adding refractory-metal carbide to improve the ablation property of carbon/carbon(C/C) composite, which is widely used as advanced SRM throat for its characteristics of low density, high strength, super anti-ablation and anti-thermal shock properties. One of the effective methods to improve the anti-ablation property of C/C composite at the temperature above 4000K is to add refractory metal carbide in its carbon matrix. The results indicate that, by the technology of impregnating resin, which containing refractory metal oxide, the C/C composite, which has 5-7% ZrC and the density is 1.90g/cm~3, shows excellent anti-ablation property.
机译:具有未冷却喷嘴的固体火箭发动机(SRM)产生的热,化学和机械环境在火箭喷嘴的开发中引入了许多材料问题。尤其是喉管材料必须承受高温,机械载荷,热冲击,化学腐蚀以及对尺寸稳定性的高度要求。用作喉咙的材料包括难熔金属,陶瓷,石墨和纤维增强塑料等,可以满足早期SRM的需求,但其中一些密度高,某些材料不能承受热冲击,某些材料可以烧蚀。它们容易导致大的惰性质量,从而限制了喷嘴效率的提高。关于添加难熔金属碳化物以改善碳/碳(C / C)复合材料的烧蚀性能的文献,由于其低密度,高强度,超级抗烧蚀和抗腐蚀的特性而被广泛用作高级SRM喉咙。 -热冲击性能。改善C / C复合材料在4000K以上温度下的抗烧蚀性能的有效方法之一是在其碳基体中添加难熔金属碳化物。结果表明,采用含难熔金属氧化物的树脂浸渍技术,ZrC含量为5-7%,密度为1.90g / cm〜3的C / C复合材料具有良好的抗烧蚀性能。

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