Effect of hafnium carbide content on the ablative performance of carbon/carbon composites as rocket throats
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摘要: 将炭毡浸渍于饱和的HfOCl2 · 8H2O乙醇溶液中，经600℃热处理形成HfO2/C复合材料，然后采用热梯度化学气相沉积工艺在2100℃进行致密化和石墨化处理使HfO2 转化为 HfC而得到碳化铪(HfC)改性、整体炭毡增强的炭/炭(HfC-C/C)复合材料整体喉衬。利用小型固体火箭发动机试车台装置，在7MPa 、 3200℃烧蚀 3s以测定HfC含量对喉衬烧蚀性能的影响。 结果表明,HfC质量分数为5.7%的HfC-C/C喉衬线烧蚀率减小了25.2%;HfC质量分数为8.7%的HfC-C/C喉衬线烧蚀率减小了49.6%。 同时,当HfC质量分数为5.7%时,HfC-C/C喉衬出现了以恒定线烧蚀率为特征的稳态烧蚀阶段,且该阶段的持续时间随HfC含量的增加而增加。Abstract: Hafnium carbide (HfC) modified carbon/carbon (HfC-C/C) composites were prepared by impregnating carbon felts with a saturated HfOCl2 · 8H2O ethanol solution and heat treating at 600℃ to form HfO2/C composites that were then densified with pyrocarbon by chemical vapor infiltration and graphitized at 2 100℃ to convert HfO2 into HfC. The HfC-C/C composites as rocket throats were ablated at 7 MPa and around 3 200℃ for 3 s by an experimental solid rocket motor. Results showed that the HfC-C/C composites with HfC contents more than 5.7 mass% had a stable period with a constant ablation rate and the duration of this period increased with HfC content. The overall ablation rate was decreased by 25.2 and 49.6% for the composites having 5.7 and 8.7 mass% HfC respectively as compared with the composite with 2.5 mass% HfC.
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Key words:
- Carbon/carbon composites /
- Solid rocket motor /
- Hafnium carbide /
- Ablation performances
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