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An analytical study of reusable flight-weight cryogenic propellant tank designsThermostructural analyses of reusable flight-weight cryogenic tanks for a vertically launched space vehicle have been conducted. An analytical procedure was developed for sizing the tank structure, cryogenic insulation, and thermal protection system. Unstiffened, integrally-stiffened, and honeycomb core sandwich tank skins using aluminum or stainless steel materials were compared for their ability to meet design criteria at least weight. Cryogenic insulation systems were also evaluated, including closed-cell cryogenic foams and evacuated honeycomb core. The results indicate that a 400 F foam-insulated unstiffened-skin aluminum tank structure is the lightest structure for either LOX or LH2 tanks that meet the selected design criteria, but only two to four percent lighter than a stiffened aluminum tank.
Document ID
19840048896
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Taylor, A. H.
(NASA Langley Research Center Hampton, VA, United States)
Jackson, L. R.
(NASA Langley Research Center Hampton, VA, United States)
Cerro, J. A.
(Kentron International, Inc. Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
May 1, 1984
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 84-0865
Accession Number
84A31683
Distribution Limits
Public
Copyright
Other

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