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Pressure drops in the non-isothermal sloshing of liquid nitrogen and liquid hydrogen were experimentally investigated. Heat and mass transfer indicated by the pressure change induced by violent sloshing in the cryostat driven by the mechanical exciter were successfully obtained. Based on the visualized image of liquid motion, it was found that splash and wavy surface induced by violent sloshing of liquid should enhance heat transfer around liquid surface and result in pressure drop. It was also suggested that the instability of singlecomponent system with different temperature between the gaseous and liquid phase could make the pressure control more difficult. Nomenclature  : density [ kg/m 3 ] p : static pressure [ Pa ] T : static temperature [ K ] e : internal energy [ J/kg ] u  : velocity [ m/s ] g  : gravity acceleration [ m/s 2 ] q  : heat flux [ W/m 2 ] C p , C v : specific heat at constant p or  [ J/(kg･K) ]  : viscosity coefficient [ Pa･s ] k : thermal conductivity [W/(m 2 ･K) ]  : surface tension [ N/m ] D : diameter of vessel [ m ] t : time [ sec ]

The Japan Aerospace Exploration Agency launched the S-310-43 sounding rocket from the Uchinoura Space Center on Aug. 04, 2014 for the purpose of investigating such behavior as boiling and flow of cryogenic liquid rocket propellant in an environment simulating coasting flight on orbit by using the sounding rocket's sub-orbital ballistic flight. In the low-gravity state, the cryogenic fluid (liquid nitrogen) was introduced into the test sections of similar shapes to the flow channels in the cryogenic propulsion systems. The boiling of liquid nitrogen inside the test-sections and the transition of flow regimes from gas/liquid two-phase flow to liquid mono-phase flow were visualized. The temperatures, pressures and void fractions of each channels were measured as well. Development of the experimental equipment for S-310-43 sounding rocket is described in this paper.