| This thesis proposes a concept of re-supplying propellant in orbit by employing a pressure differential methodology. The transfer process involves venting the ullage gas from the receiving tank to establish the pressure difference and transferring the propellant from the supply tank to the receiving tank. Without the effect of gravity, the gas and liquid are not forced to settle in any predictable location inside a given boundary. This poses a problem in determining an appropriate location for venting the ullage gas. The solution is to establish a condition where the gas is distinctly separated from the liquid and is forced in a known location. To achieve this condition, a concept has been developed by a method of phase separation of the ullage gas/liquid mixture. The design and analysis presented herein demonstrate the feasibility of venting ullage gas in a microgravity environment. |
