Effect of combustion gas mass flow rate on carbon/carbon composite nozzle ablation in a solid rocket motor
Effect of combustion gas mass flow rate on carbon/carbon composite nozzle ablation in a solid rocket motor
复制标题
固体火箭发动机中燃烧气体质量流量对碳/碳复合喷嘴烧蚀的影响
DOI：
10.1016/j.carbon.2011.11.034
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发表时间：
2012-04-01
期刊：
影响因子：
10.9
通讯作者：
Qin, Fei
中科院分区：
文献类型：
--
作者：
Peng, Li-na;He, Guo-qiang;Qin, Fei
制备了4向碳/碳复合材料。在固体火箭发动机燃烧环境中，研究了四向碳/碳复合材料喷管的烧蚀问题。利用扫描电镜对烧蚀表面和微观结构进行了观察，并对烧蚀机理进行了探讨。结果表明，随着燃气质量流量的增加，喷管后缩率增大。复合材料的烧蚀归因于碳和氧化物种之间的非均相反应。这与壁温较高时喷嘴烧蚀主要受扩散限制的事实是一致的。烧蚀过程中，复合材料表面形成锥形纤维、环形沟槽和带有凹坑和弹坑的层状基体。球形碳颗粒在表面的沉积归因于由环氧树脂和二氧化硅组成的推进剂抑制剂层在高质量流量下热解时形成挥发性烃，该抑制剂层用于抑制火箭发动机固体推进剂的燃烧。(C)2011爱思唯尔有限公司保留所有权利。
A 4-direction carbon/carbon composite was produced. The ablation of 4-direction carbon/carbon composite nozzles was investigated in the combustion environment of a solid rocket motor. The ablation surface and microstructure were examined by scanning electron microscopy and the ablation mechanism was also studied. The results show that the nozzle recession rate increases with the increasing mass flow rate of combustion gases. The ablation of the composite was attributed to the heterogeneous reactions between carbon and oxidizing species. This is consistent with the fact that the nozzle ablation was mainly diffusion-limited when the wall temperature was high. The ablation of the composite resulted in cone-shape fibers, ring-shaped grooves and a lamellar matrix with pits and craters on the surfaces. The deposition of spherical carbon particles on the surface was attributed to the formation of volatile hydrocarbons during the pyrolysis of the propellant inhibitor layer, which consisted of epoxy resin and silica and was used for inhibiting combustion of the solid-propellant in rocket motor, under a high mass flow rate. (C) 2011 Elsevier Ltd. All rights reserved.