固体火箭发动机复合结构喷管温度场与应力场理论计算  

THEORETICAL CALCULATION OF COMPLEX NOZZLE'S TEMPERATURE PROFILE AND STRESS PROFILE IN SOLID ROCKET MOTOR

作　　者：孙菊芳[1] 孙冰[1] 相升海 

机构地区：[1]北京航空航天大学动力系

出　　处：《推进技术》1994年第1期23-31,22,共10页Journal of Propulsion Technology

摘　　要：对某长时间工作的固体火箭发动机复合结构喷管的二维轴对称瞬态温度场及二维轴对称准静态应力场进行了理论预估。温度场的计算采用时间域上的有限差分及空间域上的有限元相结合的方法。应力场的计算采用以位移作为未知量的有限元法。计算中考虑了材料的方向性及物性参数随温度的变化，采用变带宽一维压缩存贮刚度矩阵，节约了大量的内存。计算结果与试验结果吻合较好。In this paper, two-dimension axial symmetrical instantaneous temperature profile and two-dimension axial symmetrical similar static stress profile are calculated in the complex nozzle of a solid rocket motor with long worktime. The method to calculate temperature profile is to combine finite difference of time with finite element of space. The method to calculate stress profile is the finite element one that displacement is treated as unknown parameter. Directionality of material and variation of materail parameter with temperature are considered in the calculation. Rigidity matrix is stored after the matrix is cut down with different width in one dimension array in the calculation. It saves a large number of memory cells. Calculated result is basically identical with tested result.

关 键 词：火箭发动机 喷管 温度分布 

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]