Analysis of cryogenic propellant behaviour in microgravity and low thrust environments

Abstract

Understanding the behaviour and response of cryogenic propellants during spacecraft flight operations (e.g., engine restart and fluid transfer) is an extremely important aspect of vehicle design. Accurate predictions of fluid motion and slosh amplification are needed to ensure proper settling prior to engine burn and effective vehicle control throughout all phases of the mission. To augment analyses of this type, Marshall Space Flight Center (MSFC) recently acquired FLOW-3D, a CFD package developed by Flow Sciences Inc. This paper describes a recent validation in which FLOW-3D model predictions were compared with MSFC drop tower test data. Although the tests were originally conducted in the 1960s to support design and performance assessments of the Saturn S-IVB stage liquid hydrogen (LH 2) tank, the data have proven useful for verifying the accuracy of the FLOW3D model.