Numerical study on effects of temperature and pressure on nozzle damping characteristics in rocket motor

In order to explore the impact of gas temperature and working pressure on the nozzle damping characteristics of solid rocket motor, different cases were numerically studied via the pulse decay method based on the two-dimensional model of the Buffum's motor. The aim of this study is to improve the reliability of cold flow experimental test and provide the corresponding theoretical guidance of unstable combustion research. The results indicate that the gas temperature has cooperative effects on the nozzle damping while the working pressure has little influence. After the pulse is cut off, the pressure oscillation decays faster with the gas temperature increasing, and the nozzle damping attenuation coefficient is also greater. The working pressure has little influence on the pressure oscillation decay rate, and the nozzle damping attenuation coefficient is almost unchanged under various working pressure.