旋转条件下大长径比固体火箭发动机三维内流场数值模拟

Three Dimensional Internal Flow Field Numerical Simulation of High Length-Diameter Ratio SRM Under Spinning Condition

摘要:

根据燃面的平行层推移原理,获得了某大长径比固体火箭发动机装药燃面变化过程。采用有限体积法计算了发动机在旋转飞行状态下的三维稳态流场,着重分析了不同时刻药柱开槽部分和燃烧室尾部的流速、流迹分布及其对发动机正常工作的影响,认为发动机尾部热防护以及药柱悬臂段强度是保证其正常工作的关键因素。

Abstract:

Based on parallel-layer regression principle,the change process of grain burning surface was obtained. The three dimensional internal steady flow field of the motor was simulated numerically under the spinning con. dition by using finite elements method,gas velocity and path lines at the groove and tail of combustion chamber during different period were analyzed in detail. The influence of the flow field on the motor working process was analyzed. It was believed that the key factors to the motor safety were thermal protection at the tail of the combustion chamber and strength of the cantilever part of the grain.