Abstract
The objective of this study is to investigate the effect of sloshing in the propellant tank on the discharge flow during re-ignition of the space vehicle. A parametric study was conducted considering phase interface, vapor ingestion phenomenon, and velocity/pressure fluctuations in the discharge pipe. The vapor ingestion, which can develop during the propellant discharge, occur easily with smaller thrust and lower boundary surface height. When dip occur at the face interface, sloshing had the effect of lowering the phase interface periodically, resulting in a shorter vapor ingestion time and less usable residual propellant. The velocity fluctuations in the discharge pipe cross section due to sloshing were expected to generate a pump head/torque performance and a lateral force on the pump shaft meaningfully. In addition, in the case of pressure fluctuations, sloshing did not directly affect pump performance because the scale of pressure fluctuations due to sloshing is small compared to the scale of one caused by pump operation.
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