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Lattice Boltzmann Method for Spacecraft Propellant Slosh SimulationA scalable computational approach to the simulation of propellant tank sloshing dynamics in microgravity is presented. In this work, we use the lattice Boltzmann equation (LBE) to approximate the behavior of two-phase, single-component isothermal flows at very low Bond numbers. Through the use of a non-ideal gas equation of state and a modified multiple relaxation time (MRT) collision operator, the proposed method can simulate thermodynamically consistent phase transitions at temperatures and density ratios consistent with typical spacecraft cryogenic propellants, for example, liquid oxygen. Determination of the tank forces and moments relies upon the global momentum conservation of the fluid domain, and a parametric wall wetting model allows tuning of the free surface contact angle. Development of the interface is implicit and no interface tracking approach is required. Numerical examples illustrate the method's application to predicting bulk fluid motion including lateral propellant slosh in low-g conditions.
Document ID
20150006882
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Orr, Jeb S.
(Draper (Charles Stark) Lab., Inc. Huntsville, AL, United States)
Powers, Joseph F.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Yang, Hong Q.
(Computational Fluid Dynamics Research Corp. Huntsville, AL, United States)
Date Acquired
April 29, 2015
Publication Date
January 30, 2015
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
M15-4348
AAS 15-091
Meeting Information
Meeting: 2015 American Astronautical Society (AAS) Guidance, Navigation, and Control Conference
Location: Breckenridge, CO
Country: United States
Start Date: January 30, 2015
End Date: February 4, 2015
Sponsors: American Astronautical Society
Funding Number(s)
CONTRACT_GRANT: NNM12AA41C
Distribution Limits
Public
Copyright
Public Use Permitted.
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