轴棒法编织C/C复合材料喉衬烧蚀性能分析  

Analysis on Ablation Properties of Axial Carbon Rod Woven 4DC/C Composite Throat

作　　者：吴书锋[1] 张玲[1] 周绍建[1] 嵇阿琳[1] 杨杰[1] 周红英[1] 刘建军 

机构地区：[1]西安航天复合材料研究所,西安710025 [2]高性能碳纤维制造及应用国家地方联合工程研究中心,西安710089

出　　处：《材料导报》2013年第22期62-65,共4页Materials Reports

基　　金：国家973项目(2011CB605801)

摘　　要：对轴棒法编织碳/碳(C/C)复合材料喉衬进行固体火箭发动机(SRM)地面点火试验,采用扫描电子显微镜(SEM)对烧蚀后喉衬入口部位、喉部、出口部位的烧蚀形貌进行分析。结果表明,在9.362MPa压强下,轴棒法编织C/C喉衬烧蚀性能稳定、均匀,烧蚀后型面光滑,平均线烧蚀率为0.2569mm·s-1,是适用于高工作压强、大流量的SRM喷管喉衬材料。C/C喉衬不同部位呈现出不同的烧蚀形貌。A firing test was carried out to analyze the ablation properties of axial carbon rod woven 4D carbon/ carbon（C/C） composite throat. The ablation morphologies of its different parts （entrance part, throat and exit part） were investigated by scanning electron microscopy （SEM）. The results showed that under the pressure of about 9. 362 MPa, the axial carbon rod woven 4D C/C throats composite have low ablation rates of about 0. 2569 ram s-1 and homogeneous properties, and their contours are smooth. The material can be applied for high-pressure and high-flow rate nozzle of solid rocket motor. The ablation morphologies of each part were different.

关 键 词：轴棒法编织 C C复合材料 喉衬 点火试验 烧蚀性能 

分 类 号：TB332[一般工业技术—材料科学与工程] V254.2[航空宇航科学与技术—航空宇航制造工程]