Simulating processes in launch vehicle propulsion systems in the presence of longitudinal oscillation damper

The paper puts forward a math model for conducting preliminary engineering evaluations of a launch vehicle rocket stage propulsion system parameters in the presence of a longitudinal oscillation damper installed in the feed line to prevent propellant oscillations, which could cause pressure buildup in the feed line, exceed proof-test pressure, and, eventually, result in the feed line failure. Results of analyses done in accordance with the math model proposed in the paper, make it possible to come up with preliminary estimates for parameters of both the launch vehicle rocket stage propulsion system, and the damper volumetric stiffness over the entire run of the launch vehicle main engine. This, in turn, makes it possible to validate the propulsion system operational integrity in the presence of a damping system. The paper considers methods for evaluating the gas-liquid mixture flow rates through the damper venting system, and estimates the critical height of a propellant component above the vent exit level during vortex formation.