The performance of a 200 W class Hall thruster was evaluated. Performance measurements were taken at power levels between 90 W and 250 W. At the nominal 200 W design point, the measured thrust was 11.3 mN. and the specific impulse was 1170 s excluding cathode flow in the calculation. A laboratory model 3 mm diameter hollow cathode was used for all testing. The engine was operated on laboratory power supplies in addition to a breadboard power processing unit fabricated from commercially available DC to DC converters.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Test Results of a 200 W Class Hall Thruster


    Beteiligte:
    D. Jacobson (Autor:in) / R. S. Jankovsky (Autor:in)

    Erscheinungsdatum :

    1999


    Format / Umfang :

    14 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Test results of a 200W class Hall thruster

    Jacobson, David / Jankovsky, Robert | AIAA | 1998


    Test Results of a 200 W Class Hall Thruster

    Jacobson, David / Jankovsky, Robert S. | NTRS | 1999


    Test Results of a 200 W Class Hall Effect Thruster

    Jacobson, D. / Jankovsky, R. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 1998


    Performance Test Results of the NASA-457M v2 Hall Thruster

    Soulas, George / Haag, Thomas / Herman, Daniel et al. | AIAA | 2012


    50 KW CLASS KRYPTON HALL THRUSTER PERFORMANCE

    Jacobson, D. T. / Manzella, D. H. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 2003