双脉冲固体火箭发动机隔塞运动特性

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.