Hall Thruster Technology for NASA Science Missions

The performance of a prototype Hall thruster designed for Discovery-class NASA science mission applications was evaluated at input powers ranging from 0.2 to 2.9 kilowatts. These data were used to construct a throttle profile for a projected Hall thruster system based on this prototype thruster. The suitability of such a Hall thruster system to perform robotic exploration missions was evaluated through the analysis of a near Earth asteroid sample return mission. This analysis demonstrated that a propulsion system based on the prototype Hall thruster offers mission benefits compared to a propulsion system based on an existing ion thruster.

[1]  Lee S. Mason,et al.  Preliminary Performance Results of the High Performance Hall System SPT-140 , 2000 .

[2]  Michael J. Patterson,et al.  Development of an Ion Thruster and Power Processor for New Millennium's Deep Space 1 Mission , 1997 .

[3]  David Manzella,et al.  Performance of Solar Electric Powered Deep Space Missions Using Hall Thruster Propulsion , 2005 .

[4]  V. Khayms,et al.  4.5 KW Hall Thruster System Qualification Status , 2004 .

[5]  Michael J. Patterson,et al.  Next: NASA's Evolutionary Xenon Thruster development status , 2003 .

[6]  Michael J. Patterson,et al.  A Review of Testing of Hollow Cathodes for the International Space Station Plasma Contactor , 2001 .

[7]  Michael J. Patterson,et al.  Ion Propulsion Development Projects in US: Space Electric Rocket Test I to Deep Space 1 , 2001 .

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

[9]  Michael J. Patterson,et al.  Development of a Hollow Cathode Assembly for the High Voltage Hall Accelerator , 2005 .

[10]  David Y. Oh.  Evaluation of Solar Electric Propulsion Technologies for Discovery Class Missions , 2005 .

[11]  John R. Brophy,et al.  Status of the Extended Life Test of the Deep Space 1 Flight Spare Ion Engine After 30,000 Hours of Operation , 2003 .

[12]  Hani Kamhawi.  Development of a Hollow Cathode for the High Voltage Hall Accelerator , 2007 .

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

[14]  Staffan Persson,et al.  SMART-1 mission description and development status , 2002 .

[15]  V. Kim.  Main Physical Features and Processes Determining the Performance of Stationary Plasma Thrusters , 1998 .

[16]  George C. Soulas,et al.  Plasma contactor technology for Space Station Freedom , 1993 .

[17]  Timothy R. Sarver-Verhey.  28,000 Hour Xenon Hollow Cathode LifeTest Results , 1997 .

[18]  Kevin Witzberger,et al.  NASA's 2004 In-Space Propulsion Refocus Studies for New Frontiers Class Missions , 2005 .

[19]  John M. Sankovic,et al.  Evaluation of Low Power Hall Thruster Propulsion , 1996 .

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

[21]  David H. Manzella,et al.  NASA's 2004 Hall Thruster Program , 2013 .

[22]  Richard G. Wilmoth,et al.  Aerodynamics of Stardust Sample Return Capsule , 1997 .

[23]  Angioletta Coradini,et al.  Dawn: a journey to the beginning of the solar system , 2002 .

[24]  N. Maslennikov,et al.  INTEGRATED TEST OF AN SPT-100 SUBSYSTEM , 1997 .