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Ion-thruster propellant utilization

Author: Harold R Kaufman; United States. National Aeronautics and Space Administration.; Lewis Research Center.
Publisher: [Washington, D.C.] : [National Aeronautics and Space Administration] ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971.
Series: NASA technical note, D-6591.
Edition/Format:   eBook : Document : National government publication : EnglishView all editions and formats
Summary:
The evaluation and understanding of maximum propellant utilization, with mercury used as the propellant are presented. The primary-electron region in the ion chamber of a bombardment thruster is analyzed at maximum utilization. The results of this analysis, as well as experimental data from a range of ion-chamber configurations, show a nearly constant loss rate for unionized propellant at maximum utilization over a  Read more...
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Additional Physical Format: Print version:
Kaufman, Harold R.
Ion-thruster propellant utilization.
[Washington, D.C.] : [National Aeronautics and Space Administration] ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971
(OCoLC)643028070
Material Type: Document, Government publication, National government publication, Internet resource
Document Type: Internet Resource, Computer File
All Authors / Contributors: Harold R Kaufman; United States. National Aeronautics and Space Administration.; Lewis Research Center.
OCLC Number: 785205141
Notes: "December 1971."
Prepared at Lewis Research Center.
Reproduction Notes: Electronic reproduction. [S.l.] : HathiTrust Digital Library, 2011. MiAaHDL
Description: 1 online resource (56 pages) : illustrations.
Details: Master and use copy. Digital master created according to Benchmark for Faithful Digital Reproductions of Monographs and Serials, Version 1. Digital Library Federation, December 2002.
Series Title: NASA technical note, D-6591.
Responsibility: by Harold R. Kaufman.

Abstract:

The evaluation and understanding of maximum propellant utilization, with mercury used as the propellant are presented. The primary-electron region in the ion chamber of a bombardment thruster is analyzed at maximum utilization. The results of this analysis, as well as experimental data from a range of ion-chamber configurations, show a nearly constant loss rate for unionized propellant at maximum utilization over a wide range of total propellant flow rate. The discharge loss level of 1000 eV/ion was used as a definition of maximum utilization, but the exact level of this definition has no effect on the qualitative results and little effect on the quantitative results. There are obvious design applications for the results of this investigation, but the results are particularly significant whenever efficient throttled operation is required.

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