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Nodal Modeling of Helium Pressurization and Autogenous Pressurization and Draining using a Multi-Node-Ullage ApproachPressurized expulsion tests of liquid methane were modeled by a nodal code using a multinode ullage approach. Generalized Fluid System Simulation Program (GFSSP), a finite volume based nodal code was used to model the expulsion of liquid methane from a 1.52-meter (5 ft) diameter spherical tank by pressurizing with helium and gaseous methane. The purpose of the model was to estimate the amount of pressurant required and amount of condensation and evaporation of methane during the operation. The ullage was discretized into multiple nodes and each fluid node was connected to solid nodes. Both the fluid and solid nodes grow as the tank drains. The heat and mass transfer between fluid and solid node in the tank ullage was computed. The heat and mass transfer between the bottom ullage node and the liquid methane was also computed. The model predictions were compared with data from twelve test cases. The predicted pressurant consumption for helium pressurization compares with test data with a Mean Absolute Percent Error (MAPE) of 3%. For autogenous pressurization, where gaseous methane was used to pressurize liquid methane, the predicted pressurant consumption compares with a MAPE of 6%.
Document ID
20240015892
Acquisition Source
Marshall Space Flight Center
Document Type
Presentation
Authors
Andre LeClair
(Marshall Space Flight Center Redstone Arsenal, United States)
Alok Majumdar
(Marshall Space Flight Center Redstone Arsenal, United States)
Date Acquired
December 11, 2024
Subject Category
Spacecraft Design, Testing and Performance
Propellants and Fuels
Meeting Information
Meeting: AIAA SciTech Forum
Location: Orlando, FL
Country: US
Start Date: January 6, 2025
End Date: January 10, 2025
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 633369.07.01.04.62
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Nodal Model
Tank Pressurization
Cryogenic Propellant
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