Analytical Discharge Performance Model for rf and Kaufman Ion Thrusters

Simple performance model for ring and line cusp ion thrusters

AIAA Journal ◽

10.2514/3.9158 ◽

1985 ◽

Vol 23 (11) ◽

pp. 1731-1736 ◽

Cited By ~ 28

Author(s):

John R. Brophy ◽

Paul J. Wilbur

Keyword(s):

Performance Model ◽

Ion Thrusters

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Analytical Ion Thruster Discharge Performance Model

Journal of Propulsion and Power ◽

10.2514/1.26404 ◽

2007 ◽

Vol 23 (5) ◽

pp. 1055-1067 ◽

Cited By ~ 35

Author(s):

Dan M. Goebel ◽

Richard E. Wirz ◽

Ira Katz

Keyword(s):

Performance Model ◽

Discharge Performance ◽

Ion Thruster

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Analytical Ion Thruster Discharge Performance Model

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit ◽

10.2514/6.2006-4486 ◽

2006 ◽

Cited By ~ 5

Author(s):

Dan Goebel ◽

Richard Wirz ◽

Ira Katz

Keyword(s):

Performance Model ◽

Discharge Performance ◽

Ion Thruster

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Hollow Cathode and Low-Thrust Extraction Grid Analysis for a Miniature Ion Thruster

International Journal of Plasma Science and Engineering ◽

10.1155/2008/693825 ◽

2008 ◽

Vol 2008 ◽

pp. 1-11 ◽

Cited By ~ 15

Author(s):

Richard Wirz ◽

Regina Sullivan ◽

JoHanna Przybylowski ◽

Mike Silva

Keyword(s):

Hollow Cathode ◽

High Efficiency ◽

Low Thrust ◽

Discharge Performance ◽

Ion Thruster ◽

Ion Extraction ◽

Ion Thrusters ◽

Future Space ◽

Thrust Characteristics ◽

Computational Analyses

Miniature ion thrusters are well suited for future space missions that require high efficiency, precision thrust, and low contamination in the mN to sub-mN range. JPL's miniature xenon Ion (MiXI) thruster has demonstrated an efficient discharge and ion extraction grid assembly using filament cathodes and the internal conduction (IC) cathode. JPL is currently preparing to incorporate a miniature hollow cathode for the MiXI discharge. Computational analyses anticipate that an axially upstream hollow cathode location provides the most favorable performance and beam profile; however, the hot surfaces of the hollow cathode must be sufficiently downstream to avoid demagnetization of the cathode magnet at the back of the chamber, which can significantly reduce discharge performance. MiXI's ion extraction grids are designed to provide >3 mN of thrust; however, previous to this effort, the low-thrust characteristics had not been investigated. Experimental results obtained with the MiXI-II thruster (a near replica or the original MiXI thruster) show that sparse average discharge plasma densities of ∼5×1015–5×1016 m-3 allow the use of very low beamlet focusing extraction voltages of only ∼250–500 V, thus providing thrust levels as low as 0.03 mN for focused beamlet conditions. Consequently, the thrust range thus far demonstrated by MiXI in this and other tests is 0.03–1.54 mN.

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