为了研究隔离装置对脉冲固体火箭发动机的影响,文中建立了数值计算模型,针对三种隔离装置方案,进行了二、三脉冲工作状态下的三维内流场数值仿真,给出了流场物理参数分布并与试验结果验证。计算分析了隔离装置的开孔结构型式对燃烧室和隔离装置绝热层烧蚀的影响,提出了应采取的措施,计算结果可为脉冲固体火箭发动机隔离装置优化设计提供参考。

In order to study the influence of separator diaphragm on pulse solid rocket motor, simulation model was presented. Based on three types of separator diaphragms, the 3-D flow field through pulse solid rocket motor was simulated when the motor working on the second and the third pulse, and physical parameter distribution in inner flow filed was obtained and certificated by confirmatory tests. At last, the influences of the patterns and size of the holes imposed on ablative shielding of combustion chamber and separator diaphragm ware analyzed, the countermeasures were offered. The conclusions of this paper can serve as references for optimal design of separator diaphragm.