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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    Titel :

    Ion-thruster propellant utilization


    Beteiligte:
    Kaufman, H. R. (Autor:in)

    Erscheinungsdatum :

    01.12.1971


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Ion-thruster propellant utilization

    Kaufmann, Harold R. | TIBKAT | 1971


    lon-Thruster Propellant Utilization

    HAROLD R. KAUFMAN | AIAA | 1972


    Ion-Thruster Propellant Utilization

    H. R. Kaufman | NTIS | 1971


    Ion-thruster propellant utilization.

    Kaufman, H. R. | NTRS | 1972