| タイトル | Mass study for modular approaches to a solar electric propulsion module |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770012214 |
| 著者（英） | Cake, J. E.; Sharp, G. R.; Oglebay, J. C.; Shaker, F. J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1977-03-01 |
| 言語 | eng |
| 内容記述 | The propulsion module comprises six to eight 30-cm thruster and power processing units, a mercury propellant storage and distribution system, a solar array ranging in power from 18 to 25 kW, and the thermal and structure systems required to support the thrust and power subsystems. Launch and on-orbit configurations are presented for both modular approaches. The propulsion module satisfies the thermal design requirements of a multimission set including: Mercury, Saturn, and Jupiter orbiters, a 1-AU solar observatory, and comet and asteroid rendezvous. A detailed mass breakdown and a mass equation relating the total mass to the number of thrusters and solar array power requirement is given for both approaches. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 77N19158
NASA-TM-X-3473
E-8800 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/182960 |
