| タイトル | Gallium Electromagnetic (GEM) Thruster Performance Measurements |
| 本文（外部サイト） | http://hdl.handle.net/2060/20090038576 |
| 著者（英） | Burton, Rodney L.; Thomas, Robert E.; Polzin, K. A. |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2009-09-20 |
| 言語 | eng |
| 内容記述 | Discharge current, terminal voltage, and mass bit measurements are performed on a coaxial gallium electromagnetic thruster at discharge currents in the range of 7-23 kA. It is found that the mass bit varies quadratically with the discharge current which yields a constant exhaust velocity of 20 km/s. Increasing the electrode radius ratio of the thruster from to 2.6 to 3.4 increases the thruster efficiency from 21% to 30%. When operating with a central gallium anode, macroparticles are ejected at all energy levels tested. A central gallium cathode ejects macroparticles when the current density exceeds 3.7 10(exp 8) A/square m . A spatially and temporally broad spectroscopic survey in the 220-520 nm range is used to determine which species are present in the plasma. The spectra show that neutral, singly, and doubly ionized gallium species are present in the discharge, as well as annular electrode species at higher energy levels. Axial Langmuir triple probe measurements yield electron temperatures in the range of 0.8-3.8 eV and electron densities in the range of 8 x 10(exp )20 to 1.6 x 10(exp 21) m(exp -3) . Triple probe measurements suggest an exhaust plume with a divergence angle of 9 , and a completely doubly ionized plasma at the ablating thruster cathode. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | IEPC-2009-233
M09-0810 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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