The 0.6 kW Electric Propulsion Demonstration Module (EPDM) flight thruster system was tested in a large vacuum facility for performance measurements and functional checkout. The thruster was operated at a xenon flow rate of 3.01 mg/s, which was supplied through a self-contained propellant system. All power was provided through a flight-packaged power processing unit, which was mounted in vacuum on a cold plate. The thruster was cycled through 34 individual startup and shutdown sequences. Operating periods ranged from 3 to 3600 seconds. The system responded promptly to each command sequence and there were no involuntary shutdowns. Direct thrust measurements indicated that steady state thrust was temperature sensitive, and varied from a high of 41.7 mN at 16 C, to a low of 34.8 mN at 110 C. Short duration thruster firings showed rapid response and good repeatability.


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    Title :

    RHETT/EPDM Performance Characterization


    Contributors:
    Haag, T. (author) / Osborn, M. (author)

    Conference:

    International Electric Propulsion Conference ; 1997 ; Cleveland, OH, United States


    Publication date :

    1998-06-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    RHETT/EPDM Flight Hollow Cathode

    Manzella, David / Patterson, Michael / Pastel, Michael | NTRS | 1997