双脉冲固体火箭发动机隔塞运动特性

以双脉冲固体火箭发动机隔塞的运动过程为研究对象,搭建了脉冲隔离装置冷气冲击实验平台,获得了隔塞在Ⅰ脉冲燃烧室中的运动规律。采用动态结构嵌套网格方法,对隔塞的运动过程进行了数值模拟,分析了隔塞运动过程中流场结构,揭示了隔塞运动规律的形成机制。研究结果表明:对于单孔隔板,隔塞在燃烧室中沿轴向平稳运动,随着驱动压强的上升,隔塞运动的初始加速度增加,运动速度有所上升;对于多孔隔板,由于隔板级间孔和隔塞对燃烧室内流场结构的干扰,导致多个隔塞在Ⅰ脉冲燃烧室中的运动过程异常复杂,出现转动和翻覆现象;且随着时间的推移,隔塞的运动速度、姿态和位置差异逐渐增大,合理的隔板级间孔设计可以有效避免隔塞在喷管喉部处聚集。 

Characteristics of plug motion in dual pulse solid rocket motor

Taking the plug motion process of the dual pulse solid rocket motor as the research object, a cold gas impact experimental platform for the pulse separation device was built, and the motion law of the plug in the first pulse combustion chamber was obtained. The dynamic structure overset grid method was used to simulate the motion process of the plug. The flow field structure during the motion of the plug was analyzed and the formation mechanism of the plug motion law was revealed. The study results showed that for pulse separation device with one hole, the plug moved smoothly along the axial direction in the combustion chamber. As the pressure rose, the initial acceleration of the plug increased and the motion speed increased slowly. For pulse separation device with several holes, due to the interference of the hole structures and the plugs on the flow field structure in the combustion chamber, the motion process of multiple plugs in the first pulse combustion chamber was extremely complicated, presenting the phenomenon of rotation and overturning. The difference in the motion speed, posture and position of the plug gradually increased with time. A reasonable design of the hole distribution can effectively prevent the plugs from gathering at the nozzle throat.