| タイトル | Inductively coupled TI-MPD spacecraft electric propulsion |
| 著者（英） | Britt, E. J.; Pawlik, E. V.; Clark, K. E. |
| 著者所属（英） | Rasor Associates, Inc.|Princeton Univ.|Jet Propulsion Lab., California Inst. of Tech. |
| 発行日 | 1976-01-01 |
| 言語 | eng |
| 内容記述 | A nuclear electric propulsion concept using a thermionic reactor inductively coupled to a magnetoplasma-dynamic (MPD) accelerator is described and the results of preliminary analyses are presented. In this system, the thermionic generating unit operates continuously at a power level of approximately 0.4 MW, while the MPD thruster operates intermittently at higher voltages and power levels. Energy storage is provided by building up a large current in an inductor. Periodically, the charging current is interrupted and the energy stored in the magnetic field of the inductor is utilized for a short duration thrust pulse. A typical thrust pulse is characterized by a power level of 1 to 4 MWe, a duration of 1 msec, and a duty cycle of approximately 20%. Results of the preliminary analysis show that approximately 85 to 90% of the power available from the thermionic converter array can be delivered to the MPD thruster for a nominal 400 kWe system with an inductive unit suitable for a flight vehicle. Optimized values of the total specific mass of the system including the thermionic reactor, the inductor, and the MPD thruster are estimated in the range of 23 to 24 kg/kWe. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 77A12839 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/440173 |
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