Helicon plasma sources are devices that are capable of efficiently producing high-density plasmas. There is growing interest in using a helicon plasma source in space propulsion as a replacement to the direct current plasma discharge in ion engines. A radio frequency ion engine is developed that combines a helicon plasma source with electrostatic grids and a magnetically shielded anode. Thruster performance evaluation includes estimation of the discharge plasma ion density and electron temperature and measurement of the plume current density, grid currents, and thrust. The radio frequency ion engine is tested across the following operating parameter ranges: 343–600 W radio frequency power, 50–250 G magnetic field strength, 1.0 2.0 mg / s argon flow rate, and 100–600 V discharge voltage range at an operating pressure of 1.6 × 10 5 torr Ar. , discharge ion density and electron temperature range 1.5 9.3 × 10 16 m 3 and 5.4–9.9 eV, respectively. Maximum beam current extracted is 120 mA at a 600 V discharge and is primarily limited by ion impingement on the grids due to insufficient grid potentials. The maximum measured thrust is 2.77 mN with an average uncertainty of ± 3.6 mN . Further optimization of the thruster operating conditions and grid assembly can improve thruster performance.


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    Titel :

    Initial Performance Evaluation of a Gridded Radio Frequency Ion Thruster


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2014-04-21


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






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