| タイトル | Solar Thermal Upper Stage Liquid Hydrogen Pressure Control Testing and Analytical Modeling |
| 本文（外部サイト） | http://hdl.handle.net/2060/20120015773 |
| 著者（英） | Cady, E. C.; Hastings, L. J.; Jenkins, D. S.; Chandler, F. O.; Flachbart, R. H.; Lopez, A.; Grayson, G. D.; Olsen, A. D.; Pedersen, K. W. |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2012-10-01 |
| 言語 | eng |
| 内容記述 | The demonstration of a unique liquid hydrogen (LH2) storage and feed system concept for solar thermal upper stage was cooperatively accomplished by a Boeing/NASA Marshall Space Flight Center team. The strategy was to balance thermodynamic venting with the engine thrusting timeline during a representative 30-day mission, thereby, assuring no vent losses. Using a 2 cubic m (71 cubic ft) LH2 tank, proof-of-concept testing consisted of an engineering checkout followed by a 30-day mission simulation. The data were used to anchor a combination of standard analyses and computational fluid dynamics (CFD) modeling. Dependence on orbital testing has been incrementally reduced as CFD codes, combined with standard modeling, continue to be challenged with test data such as this. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | M-1345
NASA/TP-2012-217469 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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