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Modeling of pulsed propellant reorientationOptimization of the propellant reorientation process can provide increased payload capability and extend the service life of spacecraft. The use of pulsed propellant reorientation to optimize the reorientation process is proposed. The ECLIPSE code was validated for modeling the reorientation process and is used to study pulsed reorientation in small-scale and full-scale propellant tanks. A dimensional analysis of the process is performed and the resulting dimensionless groups are used to present and correlate the computational predictions for reorientation performance.
Document ID
19890016807
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Patag, A. E. (Washington Univ. Saint Louis, MO., United States)
Hochstein, J. I. (Washington Univ. Saint Louis, MO., United States)
Chato, D. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1989
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-102117
E-4892
AIAA PAPER 89-2727
NAS 1.15:102117
Meeting Information
Meeting: Joint Propulsion Conference
Location: Monterey, CA
Country: United States
Start Date: July 10, 1989
End Date: July 12, 1989
Sponsors: ASEE, SAE, AIAA, ASME
Accession Number
89N26178
Funding Number(s)
CONTRACT_GRANT: NAG3-578
PROJECT: RTOP 591-23-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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