@article{oai:jaxa.repo.nii.ac.jp:00022524,
 author = {Kurishita, Yuto and Noritake, Satoshi and Matsuyama, Koichi and Masuda, Kazumi and Miyanaga, Masafumi and Himeno, Takehiro and Takata, Shinichi},
 month = {Jul},
 note = {50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference（July 28-30, 2014.), Cleveland, OH, United States., Helium solubility in propellant causes pressure drop in tank for bipropellant system.
There is a restriction that tank pressure is controlled in narrow range limited by maximum
design pressure of a component and minimum thrust to control attitude. Tank pressure
decreases with helium solubility for some tens day after tank pressurization on the ground.
It is necessary to predict the pressure drop. Analytical solubility model has been developed
as prediction method of the pressure drop. The prediction corresponds to the data of Apollo
and some satellites. However, the conventional model was assumed that the tank was static.
In H-II Transfer Vehicle (HTV), propellant sloshing occurred by movement of HTV between
buildings on the ground. Tank pressure drop of HTV could not be predicted by the
conventional model because of the sloshing. This research presents numerical solubility
model which expresses the influence of sloshing on helium solubility with solving distribution
of helium concentration., 資料番号: PA1510022000, レポート番号: AIAA 2014-3567},
 title = {HTV Numerical Simulation Model of the Helium Solubility in the Propellant},
 year = {2014}
}