喷管用整体毡C/C喉衬热结构完整性分析  

Thermal Structural Integrity Analysis of Nozzle Throat with Needled Integral Felt C/C Composites

作　　者：许玉荣 杨敏[2] 

机构地区：[1]湖北航天技术研究院总体设计所,武汉430040 [2]上海大学复合材料研究中心,上海200072

出　　处：《上海大学学报（自然科学版）》2014年第4期480-488,共9页Journal of Shanghai University:Natural Science Edition

摘　　要：采用有限元方法(finite element method,FEM)计算了固体火箭发动机(solid rocket motor,SRM)工作过程中及工作结束后的整体毡C/C复合材料喉衬的温度场及应力场,并将其应力极值与材料性能测试所得的强度极限值进行了比较分析.结果表明,在发动机工作过程中喉衬结构完整,发动机工作结束后喉衬所承受的最大轴向拉应力超出了材料的轴向拉伸强度极限,喉衬轴向受拉失效而纵向开裂.最后,通过发动机点火实验过程中及实验后喉衬的扫描电子显微镜(scanning electron microscope,SEM)分析对实验分析结果进行了验证.The temperature and stress fields of solid rocket motor （SRM） throat made of needled integral felt C/C composites during and after firing process are calculated using finite element method （FEM） in this paper. The calculated maximum stress in nozzle throat is compared with the final strength obtained in the material test. It has been found that the nozzle throat with needled integral felt C/C composites is safe during SRM firing, but the final axial tensile stress of nozzle throat after SRM firing exceeds the material tensile strength, leading to structure failure. The results are verified by SRM firing test and scanning electron microscope （SEM） analysis.

关 键 词：整体毡C/C复合材料 应力极值 失效 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]