固体火箭发动机喷管喉衬应力场的理论预估  

THEORETICAL CALCULATION ON STRESS FIELD OF NOZZLE INSERT IN SOLID ROCKET MOTOR

作　　者：孙菊芳[1] 

机构地区：[1]北京航空航天大学

出　　处：《推进技术》1989年第5期19-24,共6页Journal of Propulsion Technology

摘　　要：本文对固体火箭发动机复合结构喷管石墨喉衬在燃气压力和变温载荷作用下的瞬态应力场,采用有限元法进行了分析、计算.提供了该方法的力学模型与基本方法和算例.计算中考虑了材料的方向性.为了节约计算机内存,整体刚度矩阵(K)采用了变带宽压缩存贮法.为了验证理论计算结果的准确性,还与实验结果进行了对比,两者基本符合.The finite-element mothed is used to analyse and to calculate the tra-nsient stress field of graphite insert of composite nozzle under pressure and transient temperature loads in solid rocket motors. The mechanical models,basic methods and computation examples are presented in this paper. The anisotropy of materials is considered in the computation. A compress technique of variable bandwidth is used for the integral stiffness matrix in order to save the main storage. The computation results are compared with the experimental data and they accord with each other well.

关 键 词：火箭发动机 喷管 喷管喉部 应力分析 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]