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NASA NTRS · 20170007956

Development Status of High-Thrust Density Electrostatic Engines

Patterson, Michael J.·Haag, Thomas W.·Foster, John E.·Young, Jason A.·Crofton, Mark W.
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Abstract

Ion thruster technology offers the highest performance and efficiency of any mature electric propulsion thruster. It has by far the highest demonstrated total impulse of any technology option, demonstrated at input power levels appropriate for primary propulsion. It has also been successfully implemented for primary propulsion in both geocentric and heliocentric environments, with excellent ground/in-space correlation of both its performance and life. Based on these attributes there is compelling reasoning to continue the development of this technology: it is a leading candidate for high power applications; and it provides risk reduction for as-yet unproven alternatives. As such it is important that the operational limitations of ion thruster technology be critically examined and in particular for its application to primary propulsion its capabilities relative to thrust the density and thrust-to-power ratio be understood. This publication briefly addresses some of the considerations relative to achieving high thrust density and maximizing thrust-to-power ratio with ion thruster technology, and discusses the status of development work in this area being executed under a collaborative effort among NASA Glenn Research Center, the Aerospace Corporation, and the University of Michigan.

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Patterson, Michael J., Haag, Thomas W., Foster, John E., Young, Jason A., Crofton, Mark W.. 2017-07-28. Development Status of High-Thrust Density Electrostatic Engines. https://ntrs.nasa.gov/citations/20170007956

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