Open AccessPreliminary Results of Plasma Flow Measurements in a 2 KW Segmented Hall Thruster
Author(s) -
Yevgeny Raitses,
David Staack,
A. Dunaevsky,
L. Dorf,
N. J. Fisch
Publication year - 2003
Publication title -
osti oai (u.s. department of energy office of scientific and technical information)
Language(s) - English
Resource type - Reports
DOI - 10.2172/812923
Subject(s) - propellant , ion thruster , plasma , plume , aerospace engineering , electrically powered spacecraft propulsion , power (physics) , range (aeronautics) , arcjet rocket , current (fluid) , physics , mechanics , nuclear engineering , environmental science , electrical engineering , propulsion , engineering , meteorology , nuclear physics , quantum mechanics
A 2-kW Hall thruster was developed, built, and operated in an upgraded vacuum facility. The thruster performance and parameters of the plasma flow were measured by new diagnostics for plume measurements and plasma measurements inside the thruster channel. The thruster demonstrated efficient operation in terms of propellant and current utilization efficiencies in the input power range of 0.5-3.5 kW. Preliminary measurements of the ion energy spectra from the thruster axis region and the distribution of plasma parameters in the vicinity of the thruster exit are reported
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