In typical implementations of spacecraft electric propulsion (EP) systems the electrical ground of the EP power processing units are resistively isolated from the main spacecraft electrical ground. Telemetry measuring the potential difference between EP power processing unit and the spacecraft electrical ground is usually referred to as the “cathode common” potential. In this paper we review flight and laboratory data on natural and EP generated plasma interactions with solar arrays, present the theory of spacecraft floating potentials, show how this theory is consistent with flight data, and extend this theory to spacecraft with high power Hall effect thrusters.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Effect of Solar Array Plume Interactions on Hall Thruster Cathode Common Potentials



    Conference:

    Spacecraft Charging Technology Conference ; 2016 ; Noordwijk, Netherlands


    Publication date :

    2016-04-04


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English






    Effects of Cathode Configuration on Hall Thruster Cluster Plume Properties

    Brian Beal / Alec Gallimore / William Hargus | AIAA | 2007



    BPT Hall thruster plume characteristics

    de Grys, Kristi / Tilley, Dennis / Aadland, Randy | AIAA | 1999