The Study on Antiablative Property of C /C Composites
Received date: 2012-05-05
Online published: 2025-05-24
为了模拟固体火箭发动机绝热材料的工作环境，在氧气和煤油为燃料的燃气中加入Al2O3粒子，对炭-炭复合材料进行烧蚀试验。计算超音速燃流的温度和速度分布特性，得出超音速火焰各气动参量呈抛物线分布的规律。对试件的烧蚀形貌进行电子扫描观察和对燃烧产物进行光谱验证，并计算试件的烧蚀率，得出炭-炭复合材料在超音速火焰和高速粒子烧蚀/侵蚀不同条件下的不同的烧蚀机理。
关键词： 炭/炭复合材料; Al2O3粒子; 烧蚀/侵蚀; 超音速火焰(HVOF)
王德文 , 杨月诚 , 査柏林 , 何小鹏 . 炭-炭复合材料耐高温和高速粒子烧蚀/侵蚀研究*[J]. 弹箭与制导学报, 2013 , 33(1) : 132 -134 . DOI: 10.15892/j.cnki.djzdxb.2013.01.001
According to environment of solid rocket，C/C composites are ablated in a flame，which is produced by oxygen and aviation kero sene． In order to simulate solid rocket motor，some Al2O3 particles were appended in the flame． Through calculating the temperature field and velocity field of the HVOF，the parabola distribution of the HVOF was found． Through calculating the ablation ratios，scanning the ab lation area，and combining the flame characters，the ablating mechanisms of C/C composites were found．
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