Propellant tank is used to store the propellant in propulsion system. Propellant management device (PMD) is the key component in propellant tank to manage the liquid propellant under zero gravity. A microgravity drop tower test system was established to investigate the performance of PMD. A kind of vane type propellant tank was used for the drop tower test. Single module was used for experiment tests, and the microgravity level wass between 10^-2g0 and 10^-3g0. The anhydrous ethanol is used as analogue liquid. Different volume fraction of liquid were used to study influence of the PMD on the management performance. Changes of gas-liquid interface during the test are studied. Velocities flow along the vane of different liquid volume fraction in the tank are different at the beginning (t<0.8s). The liquid reorientation time is 0.8s when the liquid volume fraction is larger than 10%. The liquid reorientation time is prolong when the liquid volume fraction is less than 10%. The liquid climbing height along vane under microgravity increases as the volume fraction of liquid reduces. Experimental results provide a favorable reference for further optimization design of vane type propellant tank.

A trap device is defined as a closed structure which holds and provides a specific quantity of propellant using the surface tension forces. A trap in a vane-type PMD is investigated. The influence of the cone angle of the trap and flow distributions with different conditions in space are investigated. The VOF model could be used to simulate the flow distribution in a trap with zero or small gravity condition. The optimal angle for the trap is ?=45? and it has the best result of expulsion efficiency of the propellant tank. The trap can be full filled with propellant after 21 second at zero gravity condition and 37 second at north-south insurance condition. A gas bubble left in the trap at the end of the refilling process. There is no flow distribution change in the trap when the trap is full filled at reverse gravity condition and sink condition.

Unsteady flow in a high head pump-turbine was simulated using the Partially-Averaged Navier-Stokes (PANS) method. To study the improvement of "S" characteristics of a pump-turbine with misaligned guide vanes (MGV), turbulence kinetic energy production term and pressure fluctuations are numerical studied, comparing with results of pump-turbine with synchronized guide vane (SyV). Instability in the vaneless space of the model pump-turbine is analyzed based on turbulence kinetic energy equation. The maximum value of turbulence kinetic energy production(P_k ) with MGV is doubled compared with the maximum value with SyV, which are in accordance with the increase of the amplitude of pressure fluctuation compared with SyV. The change of P_k is determined by the change of the normal stress term. The change of normal stress term will influence the amplitude of pressure fluctuation. The maximum value of 3D term with MGV increases compared with the result with SyV. It may be caused by the nouniform flow with MGV.

Experiment research on liquid sloshing performance of a vane type tank used in high orbit satellite is carried out. The liquid sloshing tests of the tank without propellant management device (PMD) are developed under different liquid filling ratios. Experimental test results are in good agreement with theoretical results, which shows the reliability of test system. Liquid sloshing tests of the tank with PMD are performed with different directions and liquid filling ratios. There has a linear relationship between sloshing frequency and liquid filling ratio of vertical installation test when the liquid-gas interface is in the hemisphere. When the gas-liquid interface is in the cylindrical section, the sloshing frequency of vertical installation test remains basically unchanged. The inverted conical accumulator structure of PMD can increases the damping in the tank of vertical installation. The sloshing mass for vertical direction is less than the result of horizontal direction. Liquid sloshing results of the vane type propellant tank will provide a guidance for the design of spacecraft structure and control system.

A new nine layer film of liquid tank in China space station is used to store emiction with additive in urine treatment subsystem. It is the main material for storing strongly corrosive medium. There should be no leakage during the storing process. Compatibility of the nine layer film with emiction with additive is very important. In order to test the life of this material, experiment for compatibility test is performed. 1-liter complex film bag made by this film is designed to store the emiction with additive. The compatibility test and mechanical properties test showed that the nine layers complex film has good compatibility with emiction with additive used in in China space station. The height of nine layers film decreases by 5% after 90 days and it decreases by 13.6% after 750 days. Stretching intensity and stretching strain decrease during the storage process, while the elongation at break has no change basically. The nine layers film material offers a new method for the design and application of liquid container in space station.