NASA s In-Space Propulsion Technology Program is developing a high performance Hall thruster that can fulfill the needs of future Discovery-class missions. The result of this effort is the High Voltage Hall Accelerator thruster that can operate over a power range from 0.3 to 3.5 kW and a specific impulse from 1,000 to 2,800 sec, and process 300 kg of xenon propellant. Simultaneously, a 4.0 kW discharge power supply comprised of two parallel modules was developed. These power modules use an innovative three-phase resonant topology that can efficiently supply full power to the thruster at an output voltage range of 200 to 700 V at an input voltage range of 80 to 160 V. Efficiencies as high as 95.9 percent were measured during an integration test with the NASA103M.XL thruster. The accuracy of the master/slave current sharing circuit and various thruster ignition techniques were evaluated.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Integration Testing of a Modular Discharge Supply for NASA's High Voltage Hall Accelerator Thruster


    Contributors:

    Conference:

    31st International Electric Propulsion Conference (IEPC 2009) ; 2009 ; Ann Arbor, MI, United States


    Publication date :

    2010-02-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    NASA's Hall Thruster Program

    Jankovsky, Robert S. / Jacobson, David T. / Rawlin, Vincent K. et al. | NTRS | 2001


    NASA's Hall thruster program

    Jnkovsky, Robert / Jacobson, David / Rawlin, Vincent et al. | AIAA | 2001


    NASA's Hall Thruster Program

    R. S. Jankovsky / D. T. Jacobson / V. K. Rawlin et al. | NTIS | 2001


    NASA's Hall Thruster Program 2002

    R. S. Jankovsky / D. T. Jacobson / L. R. Pinero et al. | NTIS | 2002


    NASA's 2004 Hall Thruster Program

    Jacobson, David T. / Manzella, David H. / Hofer, Richard R. et al. | NTRS | 2004