A 2 kW Hall thruster was developed, built and operated in an upgraded vacuum facility. The thruster performance and parameters of the plasma flow were measured by new diagnostics for plume measurements and plasma measurements inside the thruster channel. The thruster demonstrated efficient operation in terms of propellant and current utilization efficiencies in the input power range of 0.5-3.5 kW. Preliminary measurements of the ion energy spectra from the thruster axis region and the distribution of plasma parameters in the vicinity of the thruster exit are reported.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Preliminary Results of Plasma Flow Measurements in a 2 kW Segmented Hall Thruster


    Beteiligte:
    Y. Raitses (Autor:in) / D. Staack (Autor:in) / A. Dunaevsky (Autor:in) / L. Dorf (Autor:in) / N. J. Fisch (Autor:in)

    Erscheinungsdatum :

    2003


    Format / Umfang :

    18 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Segmented Electrode Hall Thruster

    Kevin Diamant / James Pollard / Ronald Cohen et al. | AIAA | 2006


    Segmented Electrode Hall Thruster

    Diamant, K.D. | Online Contents | 2006


    Investigation of a Segmented Electrode Hall Thruster

    Diamant, Kevin / Pollard, James / Cohen, Ronald et al. | AIAA | 2004


    Parametric Investigations of Segmented Electrode Hall Thruster

    Raitses, Y. / Dorf, L. A. / Litvak, A. A. et al. | British Library Conference Proceedings | 1999


    Plasma Characterization of Hall Thruster with Active and Passive Segmented Electrodes

    Raitses, Yevgeny / Staack, David / Fisch, Nathaniel | AIAA | 2002