| タイトル | Inert gas ion thruster development |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800018923 |
| 著者（英） | Ramsey, W. D. |
| 著者所属（英） | Xerox Electro-Optical Systems |
| 発行日 | 1980-03-01 |
| 言語 | eng |
| 内容記述 | Two 12 cm magneto-electrostatic containment (MESC) ion thrusters were performance mapped with argon and xenon. The first, hexagonal, thruster produced optimized performance of 48.5to 79 percent argon mass utilization efficiencies at discharge energies of 240 to 425 eV/ion, respectively, Xenon mass utilization efficiencies of 78 to 95 percent were observed at discharge energies of 220 to 290 eV/ion with the same optimized hexagonal thruster. Changes to the cathode baffle reduced the discharge anode potential during xenon operation from approximately 40 volts to about 30 volts. Preliminary tests conducted with the second, hemispherical, MESC thruster showed a nonuniform anode magnetic field adversely affected thruster performance. This performance degradation was partially overcome by changes in the boundary anode placement. Conclusions drawn the hemispherical thruster tests gave insights into the plasma processes in the MESC discharge that will aid in the design of future thrusters. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 80N27424
NASA-CR-159805
XEOS-2372
IR-1 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/171998 |
