Ion thruster employing cesium on tungsten contact-ionization is described which has promise of meeting requirements for satellite attitude control and station keeping missions; configuration has been derived from concept of divergent space-charge flow between coaxial cylinders; ionizer emitting area is 1.0 sq cm (1.52-mm chord length by 6.35 cm long); power efficiences of 45% have been achieved at thrust levels of 1.56 mN (0.35 mlb) and specific impulses near 7000 sec; accelerator drain currents are on order of 2% of beam current or less.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Experimental performance of low-thrust, divergent-flow, contact-ionization electrostatic thruster


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Staggs, J.F. (Autor:in) / Lathem, W.C. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1967


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :