关键词: 多脉冲固体火箭发动机;隔层;流固耦合;点火延迟 

Abstract: The ignition process exists differences between elastomeric barrier multi-pulse solid rocket motor and common motor. In order to gain further insight into the nature of the ignition delay of elastomeric barrier multi-pulse solid rocket motor, physical and mathematical models were built, and MpCCI coupler was adopted as the data exchange platform of FLUENT and ANSYS to simulate the process of filling up the barrier with gas and the barrier deformation, and FLUENT was used to calculate the process of flame transmission and the filling process . The research supports the fact that the ignition delay increases more greatly in the multi-pulse solid rocket motor than in the traditional solid rocket motor, under the condition of the same ignition mass. The research also shows that the higher propellant burning rate goes, the shorter ignition delay becomes, while the larger of the free volume, the longer ignition delay becomes. However, the research indicates that the material of the barrier affects the ignition delay slightly. In conclusion, ignition delay can be diminished through increasing ignition mass or increasing burning rate. 

Key words: Multi-pulse solid rocket motor; Elastomeric barrier; Fluid-structure interaction; Ignition delay