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Internal Plasma Properties and Enhanced Performance of an 8 cm Ion Thruster DischargeThere is a need for a lightweight, low power ion thruster for space science missions. Such an ion thruster is under development at NASA Glenn Research Center. In an effort to better understand the discharge performance of this thruster. a version of this thruster with an anode containing electrically isolated electrodes at the cusps was fabricated and tested. Discharge characteristics of this ring cusp ion thruster were measured without ion beam extraction. Discharge current was measured at collection electrodes located at the cusps and at the anode body itself. Discharge performance and plasma properties were measured as a function of discharge power, which was varied between 20 and 50 W. It was found that ion production costs decreased by as much as 20 percent when the two most downstream cusp electrodes were allowed to float. Floating the electrodes did not give rise to a significant increase in discharge power even though the plasma density increased markedly. The improved performance is attributed to enhanced electron containment.
Document ID
19990116714
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Foster, John E. (NASA Glenn Research Center Cleveland, OH United States)
Patterson, Michael J. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1999
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
E-11813
NAS 1.15:209386
NASA/TM-1999-209386
Funding Number(s)
PROJECT: RTOP 635-1B-1B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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