| タイトル | Radioisotope Electric Propulsion Centaur Orbiter Spacecraft Design Overview |
| 本文（外部サイト） | http://hdl.handle.net/2060/20090029908 |
| 著者（英） | Dankanich, John; Sarver-Verhey, Tim; Colozza, Tony; Gilland, Jim; Hibbits, Karl; Oleson, Steve; Fiehler, Doug; Schmitz, Paul; Ostdiek, Paul; Packard, Tom; Gyekenyesi, John; Lisse, Carey; Juergens, Jeff; Parkey, Tom; Gold, Rob; Nguyen, Thahn; McGuire, Melissa; Hemminger, Joseph |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2009-07-01 |
| 言語 | eng |
| 内容記述 | Radioisotope electric propulsion (REP) has been shown in past studies to enable missions to outerplanetary bodies including the orbiting of Centaur asteroids. Key to the feasibility for REP missions are long life, low power electric propulsion (EP) devices, low mass radioisotope power systems (RPS) and light spacecraft (S/C) components. In order to determine what are the key parameters for EP devices to perform these REP missions a design study was completed to design an REP S/C to orbit a Centaur in a New Frontiers cost cap. The design shows that an orbiter using several long lived (approximately 200 kg Xenon throughput), low power (approximately 700 W) Hall thrusters teamed with six (150 W each) Advanced Stirling Radioisotope Generators (ASRG) can deliver 60 kg of science instruments to a Centaur in 10 yr within the New Frontiers cost cap. Optimal specific impulses for the Hall thrusters were found to be around 2000 sec with thruster efficiencies over 40%. Not only can the REP S/C enable orbiting a Centaur (when compared to an all chemical mission only capable of flybys) but the additional power from the REP system can be reused to enhance science and simplify communications. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | E-16578-1
AIAA Paper 2008-5179
NASA/TM-2009-215488 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/253032 |
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