| タイトル | An analytical study of reusable flight-weight cryogenic propellant tank designs |
| 著者（英） | Jackson, L. R.; Taylor, A. H.; Cerro, J. A. |
| 著者所属（英） | Kentron International, Inc.; NASA Langley Research Center |
| 発行日 | 1984-05-01 |
| 言語 | eng |
| 内容記述 | Thermostructural 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. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 84A31683
AIAA PAPER 84-0865 |
| 権利 | Copyright |
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