固体火箭发动机喷管喉衬应力场的有限元法计算  

APPLICATION OF FINITE ELEMENT METHOD TO CALCULATING STRESS FIELD IN NOZZLE INSERT OF SOLID ROCKET MOTOR

作　　者：孙菊芳[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1989年第3期245-249,共5页Journal of Aerospace Power

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二维应力场,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,整体结构刚度矩阵[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 methcxl is applied to analyzing the two-dimensional stress field in the graphite insert of a composite nozzle under pressure and transient temperature loads in a solid rocket motor. The mechanical models, basic approaches and numerical examples are presented in this paper. The anisotropy of the material is considered in the computation. A compression technique of variable bandwidth is applied to the stiffness matrix [K] of the integral structure in order to save main storage. The calculated results are agreed with the experimental data very well.

关 键 词：火箭发动机 喷管 喉衬 应力场 固体 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]