| タイトル | Performance of an electrically raised, synchronous satellite when subjected to radiation degradation effects |
| 本文（外部サイト） | http://hdl.handle.net/2060/19720005184 |
| 著者（英） | Cake, J. E.; Regetz, J. D., Jr. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1971-11-01 |
| 言語 | eng |
| 内容記述 | The use of solar electric propulsion to raise a high-power communication satellite from a low altitude, inclined circular orbit of the geosynchronous orbit is evaluated. Since the satellite ascends through the high intensity radiation belts, the power available from the solar array and therefore to the ion thrusters degrades. The performance of the solar electric stage in combination with the thrust augmented Thor/Delta launch vehicle is evaluated for two thrust steering programs. The transfer times and solar array requirements are presented for total geosynchronous payloads from 450 to 1100 kg. |
| NASA分類 | SPACE SCIENCES |
| レポートNO | 72N12833
NASA-TM-X-2420
E-6477 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/204647 |
