Abstract: An Integrated method for calculating unified flowfield in rocket motor chamber and nozzle is presented.In this paper the governing equation set describes unsteady one-dimensional flow with area change, mass addition, heat transfer and friction in both the chamber,and the nozzle.Of course,the method is also valid for calculating steady or unsteady gas-solid particle flow. The numerical results is in good agreement with the experimental data.

Key words: Solid rocket engine;Flow field;Flow equation;One-dimensional flow

摘要： 本文对固体火箭发动机燃烧室、喷管内的流场进行了统一处理.给出了考虑变截面、有摩擦、加质量、传热、非定常的一维气-固两相流动偏微分方程组.推导出的统一计算方程组可以同时获得发动机燃烧室内孔燃烧流场和喷管流场,即发动机整个内流流场;可用于定常或非定常的纯气相以及气-固两相流流场的计算.通过算例,证明计算与试验结果是十分吻合的.

关键词: 固体火箭发动机;流场;流动方程;一维流