Performance of four hollow cathode configurations with low work function inserts was evaluated in a steady-state 100 kW class applied magnetic field magnetoplasmadynamic (MPD) thruster. Two of the configurations exhibited stable discharge current attachment to the low work function inserts of the hollow cathodes. A maximum discharge current of 2250 A was attained. While the applied-field increased the performance of the thruster, at high applied fields the discharge current attachment moved from the insert to the cathode body. The first successful hollow cathode performed well in comparison with a conventional rod cathode MPD thruster, attaining a thrust efficiency with argon of close to 20 percent at a specific impulse of about 2000 s. The second successful configuration had significantly lower performance.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Preliminary test results of a hollow cathode MPD thruster


    Beteiligte:

    Kongress:

    International Electric Propulsion Conference ; 1991 ; Viareggio, Italy


    Erscheinungsdatum :

    01.01.1991


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Hollow cathode MPD thruster

    TOKI, K. / SHIMIZU, Y. / KURIKI, K. | AIAA | 1985


    Hollow Cathode Micro Thruster

    Katz, I. / Davis, V. A. / Mandell, M. J. et al. | British Library Conference Proceedings | 2000


    Hollow Cathode Micro Thruster

    Katz, Ira / Davis, V. / Mandell, M. et al. | AIAA | 2000


    A T5 Hollow Cathode Thruster: Experimental Results and Modelling

    Frollani, Daniele / Coletti, Michele / Gabriel, Stephen | AIAA | 2012


    The Secondary-Keeper Hollow Cathode Thruster

    Cooke, David L. / Vicente, Adrian / Lev, Dan et al. | AIAA | 2025