固体火箭冲压发动机补燃室绝热层烧蚀试验方法

基于自主研发的氧-煤油烧蚀试验系统，发展了一种用于固体火箭冲压发动机补燃室热结构及材料烧蚀研究的试验方法。采用该方法开展了某型室温硫化硅橡胶基绝热材料的烧蚀试验，试验分别在含氧化铝粒子侵蚀和无粒子侵蚀条件下进行，并根据SEM图对比分析了粒子对材料表面微观形貌的侵蚀效应。结果表明:无粒子侵蚀条件下的试样经烧蚀后膨胀并分层，其平均线烧蚀率为-0.025mm/s；而粒子侵蚀条件下的试样平均线烧蚀率为1.901mm/s，试样中心区域的陶瓷层被粒子完全破坏，只留下极薄的热解层和裸露的碳纤维端部，碳纤维周围的基体主胶、颗粒填料及芳纶纤维均被高速焰流氧化剥离，充分说明粒子对绝热层材料的强剥蚀破坏效应；同时也验证了该方法能较好地模拟固冲发动机补燃室内的烧蚀热环境，可用于材料配方的筛选和耐烧蚀性能测试。 

Ablation experimental method for insulation of secondarycombustion chamber in solid ducted rocket

Self-designed oxygen-kerosene ablation system was employed to propose an ablation test method for testing the ablation property of the thermal structure and material of secondary combustion chamber in solid ducted rocket (SDR). Particle-free erosion and alumina particle erosion tests were performed on the silicone rubber insulation by using this method to analyze the erosion of particles on the surface micro-morphology of the silicone rubber material. Experiment results revealed that the samples without particle erosion swelled and delaminated after ablation, whose mean linear ablation rate was -0.025mm/s; the mean linear ablation rate of the samples with particle erosion was 1.901mm/s, the ceramic layer in center of samples was destroyed by particle absolutely, only the ultrathin pyrolytic layer and the head of carbon fiber (CF) were left, while the rubber matrix, particle fillers and aramid fiber (AF) around CF were oxidized and stripped by high speed flame flow, then the intense erosion damage effect of particle on insulation had been proved. The research shows that the method can simulate the ablation thermal condition of secondary combustion chamber in SDR, meanwhile, this method can also be applied to selection of insulation formula and ablation performance test of insulating materials.