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Analysis of Tank PMD Rewetting Following Thrust ResettlingRecent investigations have successfully demonstrated closed-form analytical solutions of spontaneous capillary flows in idealized cylindrical containers with interior corners. In this report, the theory is extended and applied to complex containers modeling spacecraft fuel tanks employing propellant management devices (PMDs). The specific problem investigated is one of spontaneous rewetting of a typical partially filled liquid fuel/cryogen tank with PMD after thrust resettling. The transients of this flow impact the logistics of orbital maneuvers and potentially tank thermal control. The general procedure to compute the initial condition (mean radius of curvature for the interface) for the closed-form transient flows is first outlined then solved for several 'complex' cylindrical tanks exhibiting symmetry. The utility and limitations of the technique as a design tool are discussed in a summary, which also highlights comparisons with NASA flight data of a model propellant tank with PMD.
Document ID
20020090943
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Weislogel, M. M. (Portland State Univ. OR United States)
Sala, M. A. (Portland State Univ. OR United States)
Collicott, S. H. (Purdue Univ. West Lafayette, IN United States)
Rame, Enrique
Date Acquired
September 7, 2013
Publication Date
October 1, 2002
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NAS 1.26:211974
NASA/CR-2002-211974
E-13618
Funding Number(s)
PROJECT: RTOP 101-13-0B
CONTRACT_GRANT: NAS3-00126
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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