Abstract The thrust produced by a T6 ion engine main discharge hollow cathode was characterized using different propellants with a target-based measurement system, for discharge current values of 5–25A and a wide range of mass flow rates. The calculated values of specific impulse are far in excess of those that could be attributed to the heating of a gas to thermal equilibrium with the walls, as in a resistojet. This would suggest an operation mechanism more similar to that of an arcjet. The main scaling parameter for the specific impulse appears to be the discharge power per unit mass flow rate (specific power).

    Highlights The paper deals with the use of a hollow cathode (HC) as a stand-alone thruster. First data ever for the thrust from a HC working with xenon, argon and krypton. Thrust production mechanism is closer to that of an arcjet than of a resistojet. I sp exceeds what could be achieved from a flow in thermal equilibrium with the wall.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    The thrust generated by a T6 ion engine hollow cathode


    Beteiligte:

    Erschienen in:

    Acta Astronautica ; 102 ; 249-257


    Erscheinungsdatum :

    2014-05-06


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    The thrust generated by a T6 ion engine hollow cathode

    Gessini, Paolo | Online Contents | 2014


    A Study of the Thrust Generated by a T6 Hollow Cathode

    Gessini, Paolo / Gabriel, Stephen / Fearn, David | AIAA | 2006


    Hollow Cathode Thrust Production Mechanisms

    Grubisic, Angelo / Gabriel, S | AIAA | 2009


    Thrust measurement of a hollow-cathode discharge

    Snyder, Aaron / Banks, Bruce A. | TIBKAT | 1972


    Preliminary Thrust Characterization of a T5 Hollow Cathode

    Grubisic, Angelo / Gabriel, Steven | AIAA | 2007