Computational modeling of cryogenic propellant resupply

Abstract

A lumped-parameter computational simulation is developed, tested, and used to model a non-vented slow-fill transfer of liquid hydrogen into a spherical tank. The major components of the process are modeled as four discrete nodes: liquid, vapor, the cold wall, and the hot wall. Mass transfer, energy transfer, evaporation, and condensation processes are simulated. Proximity of the thermodynamic states of interest to the critical point preclude the use of a simple ideal gas model for the vapor if a robust model of the process is desired. An equation of state for gaseous hydrogen based on high-order polynomial approximations is adapted from the open literature. Simulation results provide temperature and pressure histories for the tank fill. The model is validated against data for non-vented tank fill published by NASA. The sensitivity of the non-vented fill process to three heat transfer coefficients is investigated and the results of that investigation are reported. With the objective of optimizing the propellant resupply process, the influence of inflow rate and terminal fill level on the tank pressure history were studied, with the results of these studies also being reported.

Publication Title

Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting

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