High Performance Power Module for Hall Effect Thrusters

Previous efforts to develop power electronics for Hall thruster systems have targeted the 1 to 5 kW power range and an output voltage of approximately 300 V. New Hall thrusters are being developed for higher power, higher specific impulse, and multi-mode operation. These thrusters require up to 50 kW of power and a discharge voltage in excess of 600 V. Modular power supplies can process more power with higher efficiency at the expense of complexity. A 1 kW discharge power module was designed, built and integrated with a Hall thruster. The breadboard module has a power conversion efficiency in excess of 96 percent and weighs only 0.765 kg. This module will be used to develop a kW, multi-kW, and high voltage power processors.

[1]  A. Gallimore,et al.  The Role of Magnetic Field Topography in Improving the Performance of High-Voltage Hall Thrusters , 2002 .

[2]  Robert S. Jankovsky,et al.  NASA's Hall Thruster Program 2002 , 2002 .

[3]  Lee S. Mason,et al.  NASA's Hall Thruster Program , 2001 .

[4]  Fred C. Lee,et al.  High-frequency resonant and soft-switching PWM converters , 1991 .

[5]  Steve Oleson.  Advanced Electric Propulsion for Space Solar Power Satellites , 1999 .

[6]  John M. Sankovic,et al.  Power Electronics Development for the SPT-100 Thruster , 1994 .

[7]  Roger M. Myers,et al.  Advanced propulsion for geostationary orbit insertion and north-south station keeping , 1995 .

[8]  Robert S. Jankovsky,et al.  Laboratory Model 50 kW Hall Thruster , 2002 .

[9]  Lanny G. Thieme,et al.  Parametric Study of Radiator Concepts for a Stirling Radioisotope Power System Applicable to Deep Space Mission , 2000 .

[10]  Steven R. Oleson.  Mission Advantages of Constant Power, Variable Isp Electrostatic Thrusters , 2000 .

[11]  Steven R. Oleson,et al.  Advanced Hall Electric Propulsion for Future In-Space Transportation , 2001 .

[12]  Steve Oleson.  Advanced propulsion for space solar power satellites , 1999 .

[13]  Lockheed Martin,et al.  The Development of a 4.5kw Hall Thruster Propulsion System Power Processing Unit , 2001 .

[14]  Steven R. Oleson.  Advanced Electric Propulsion for RLV Launched Geosynchronous Spacecraft , 1999 .

[15]  H. Declercq,et al.  Power processing unit for stationary plasma thruster , 1998 .

[16]  P. Peterson,et al.  A High Specific Impulse Two-Stage Hall Thruster with Plasma Lens Focusing , 2001 .

[17]  Bruce Pote,et al.  DC-DC Converter for Hall Thruster Plasma Discharge , 1999 .

[18]  Robert S. Jankovsky,et al.  High Voltage SPT Performance , 2001 .