A 15 cm multipole ion thruster was adapted for use with mercury propellant. During the optimization process three separable functions of magnetic fields within the discharge chamber were identified: (1) they define the region where the bulk of ionization takes place, (2) they influence the magnitudes and gradients in plasma properties in this region, and (3) they control impedance between the cathode and main discharge plasmas in hollow cathode thrusters. The mechanisms for these functions are discussed. Data from SERT II and cusped magnetic field thrusters are compared with those measured in the multipole thruster. The performance of this thruster is shown to be similar to that of the other two thrusters. Means of achieving further improvement in the performance of the multipole thruster are suggested.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    15 cm mercury multipole thruster


    Beteiligte:
    Longhurst, G. R. (Autor:in) / Wilbur, P. J. (Autor:in)

    Kongress:

    International Electric Propulsion Conference ; 1978 ; San Diego, CA, US


    Erscheinungsdatum :

    01.04.1978


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    15 cm mercury multipole thruster

    LONGHURST, G. / WILBUR, P. | AIAA | 1978


    15-cm Mercury Multipole Thruster

    Glen R. Longhurst / Paul J. Wilbur | AIAA | 1979


    15-cm Multipole Gas Ion Thruster

    Gerald C. Isaacson / Harold R. Kaufman | AIAA | 1977


    15 cm multipole gas ion thruster

    ISAACSON, G. / KAUFMAN, H. | AIAA | 1976