| タイトル | Cryogenic Propellant Management Device: Conceptual Design Study |
| 本文（外部サイト） | http://hdl.handle.net/2060/20110000503 |
| 著者（英） | Wollen, Mark; Merino, Fred; Newton, Christopher; Schuster, John |
| 著者所属（英） | Innovative Engineering Solutions |
| 発行日 | 2010-11-01 |
| 言語 | eng |
| 内容記述 | Concepts of Propellant Management Devices (PMDs) were designed for lunar descent stage reaction control system (RCS) and lunar ascent stage (main and RCS propulsion) missions using liquid oxygen (LO2) and liquid methane (LCH4). Study ground rules set a maximum of 19 days from launch to lunar touchdown, and an additional 210 days on the lunar surface before liftoff. Two PMDs were conceptually designed for each of the descent stage RCS propellant tanks, and two designs for each of the ascent stage main propellant tanks. One of the two PMD types is a traditional partial four-screen channel device. The other type is a novel, expanding volume device which uses a stretched, flexing screen. It was found that several unique design features simplified the PMD designs. These features are (1) high propellant tank operating pressures, (2) aluminum tanks for propellant storage, and (3) stringent insulation requirements. Consequently, it was possible to treat LO2 and LCH4 as if they were equivalent to Earth-storable propellants because they would remain substantially subcooled during the lunar mission. In fact, prelaunch procedures are simplified with cryogens, because any trapped vapor will condense once the propellant tanks are pressurized in space. |
| NASA分類 | Propellants and Fuels |
| レポートNO | IES Report No. 09-RPT-1004-ENG
NASA/CR-2010-216777
E-17403 |
| 権利 | Copyright, Distribution under U.S. Government purpose rights |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/249301 |
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