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.
Integration Testing of a Modular Discharge Supply for NASA's High Voltage Hall Accelerator Thruster
31st International Electric Propulsion Conference (IEPC 2009) ; 2009 ; Ann Arbor, MI, United States
2010-02-01
Report
No indication
English
NTRS | 2001
|AIAA | 2001
|NTIS | 2001
|NASA's Hall Thruster Program 2002
NTIS | 2002
|NASA's 2004 Hall Thruster Program
NTRS | 2004
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