采用ｋε双方程湍流模型，以ＳＩＭＰＬＥ 计算程式求解翼柱型装药固体火箭发动机燃烧室内三维非定常不可压流ＮＳ 方程．在建立翼柱型装药简化模型的基础上采用边界标志法来表达燃面推移，采用从二维到三维的初场给定方法结合多重网格法求出了多个时间步的非稳态流场结构．计算结果表明燃烧室内旋涡运动呈现一定的空间与时间分布，周向加质导致燃气通道横断面上轴向速度分布的极不均衡． The k-ε two-equation turbulence model was used to solve the three-dimensional unsteady incompressible NS equation in the combustion chamber of a solid propellant rocket engine with SIMPLE calculation program. Based on the establishment of the simplified model of the wing-shaped charge, the boundary-sign method is used to express the combustion surface transition. The unsteady state of multiple time steps Flow field structure. The calculation results show that the vortex motion in the combustion chamber presents a certain space and time distribution, and the circumferentially added mass leads to an extremely unbalanced axial velocity distribution on the cross section of the gas passage.