在抛物化假定基础上，从固体火箭发动机无烟、少焰研究需要出发，对喷管的内、外流场进行了数值模拟。考虑了化学平衡流和气／固两相流两种状态。在喷管内流场的计算中，采用隐式Ｂｅａｍ─Ｗａｒｍｉｎｇ格式对喷管进行空间推进求解；在喷流流场的计算中，用系数矩阵分裂方法对流场进行数值模拟。不论是内流场，还是喷流流场，燃烧产物的平衡组分都用布林克莱法进行求解，粒子运动参数都用特征线法进行求解。其中部分计算结果同实验及他人的计算结果进行了对比，两者吻合良好。 Based on the parabolic assumptions, the numerical simulation of the internal and external flow field of the nozzle is carried out from the research of smokeless and flameless solid rocket motor. Consider the chemical equilibrium flow and gas / solid two phase flow two states. In the calculation of the flow field in the nozzle, the implicit BeamWarming format is used to solve the nozzle in space. In the calculation of the flow field of the nozzle, the numerical simulation of the flow field is carried out by using the coefficient matrix splitting method. Either the internal flow field or the jet flow field, the equilibrium components of the combustion products are solved by the Brinkley method, and the particle motion parameters are solved by the characteristic line method. Some of the calculated results are compared with the results of experiments and others, and the two are in good agreement.