NASA NTRS · 19720018952
Maximum propellant utilization in an electron bombardment thruster
Abstract
Current theory and experimental data on propellant utilization in electron bombardment ion thrusters are reviewed. Because the majority of investigations have been conducted with mercury, the presentation emphasizes that propellant. The results are presented in as general a form as possible to facilitate use in areas other than space propulsion.
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Kaufman, H. R., Cohen, A. J.. 1971-10-01. Maximum propellant utilization in an electron bombardment thruster. https://ntrs.nasa.gov/citations/19720018952
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