Abstract
Many rocket launch failures are caused by engine problem, especially by the propellant feed system problem. Analysis of transient or unsteady characteristics of turbopump system is necessary on conducting rocket engine stability analysis such as POGO analysis. Dynamic characteristics of cavitating inducer isn't governed only by cavitation compliance defined as the ratio of cavity volume change rate to inducer inlet pressure change rate, but also by mass flow gain factor defined as the ratio of cavity volume change rate to inducer inlet mass flow change rate. This paper provides a new dynamic model of rocket engine LH_2 feed system and gives some stability analysis results.
