Abstract: An integral computation for unsteady compressible 1 D fluid flows with mass addition and moving boundary in combustion chamber, axi symmetric 2 D fluid flows in combustion chamber nozzle and 3 D grain geometric shape. Explicit TVD finite volume Mac Cormack scheme for time dependent N S equations was used. The results indicate the internal ballistics in series dual burning rate grain motor and the distribution of axi symmetric 2 D flow parameters in the chamber nozzle.

Key words: Computational fluid dynamics;Solid propellant rocket engine;Interior ballistic calculation;Integrated design

摘要： 对一维的加质燃烧室流场、轴对称的二维喷管内流场和高燃速药柱燃烧完成后的燃烧室二维内流场以及三维药柱几何做了一体化计算。应用轴对称的N S方程、TVD有限体积法的显式MacCormack格式 ,对燃烧室后段及长尾喷管跨声速流场进行求解 ,得到了双燃速内弹道性能和轴对称二维流场中燃气参数的分布。结果具有较高的精度 ,并为进一步的燃烧室和喷管热结构分析提供数值依据。

关键词: 计算流体动力学,固体推进剂火箭发动机;内弹道计算;一体化设计