A key objective of the cryogenic fluid management of the spacecraft propulsion system is to develop the technology necessary for acquisition or positioning of liquid outflow or vapor venting. In this paper, numerical simulation of positive liquid acquisition is attempted by introducing reverse gravity acceleration, resulting from the propulsive thrust of auxiliary engines, which exceeds critical value for the initiation of geyser. Based on the computer simulation of flowfields during the course of fluid reorientation, six dimensionless parameters resulted in this study. It shows that these parameters hold near-constant values through the entire ranges of liquid filled levels, from 30-80%, during the course of fluid reorientation. D f 8i go h v fm Nomenclature = geyser initiation acceleration, cm/s 2 = scale flow acceleration associated with maximum velocity (crii/s 2 ), defined by Eq. (5) = diameter of propellant tank, cm = frequency of impulsive thrust, Hz = geyser initiation gravity level, go = normal Earth gravitational acceleration, 9.81 m/s 2 = average liquid height, cm = maximum liquid height, cm = height of propellant tank, cm = scale length of maximum liquid height (cm), defined byEq. (4) -average free-fall time, s = time for observing maximum flow velocity, s = liquid reaching tank bottom time, s = average free-fall velocity (cm/s), defined by Eq. (2) = free-fall velocity from maximum liquid height (cm/s), defined by Eq. (3) = maximum flow velocity, cm/s

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