In-Space Propulsion High Voltage Hall Accelerator Development Project Overview

NASA’s Science Mission Directorate In-Space Propulsion Technology Project is funding the development of a high specific impulse long life Hall thruster. The goal of the high voltage Hall accelerator (HiVHAc) project is to develop a flight-like, engineering model (EM) Hall thruster that can meet future NASA science mission requirements. These requirements are met by a thruster that operates over an input power range from 0.3 to 3.5 kW, attains specific impulses from 1,000 to 2,700 seconds, and processes at least 300 kg of xenon propellant at full power. To demonstrate the HiVHAc project goal, two laboratory thrusters have been built and tested. The latest laboratory thruster, the NASA-103M.XL, incorporated a life-extending discharge channel replacement innovation and has been operated for approximately 5,000 hours at a discharge voltage of 700 volts. In 2007, NASA Glenn Research Center teamed with Aerojet to design and manufacture a flight-like HiVHAc EM thruster which incorporated this life-extending channel replacement innovation. The EM thruster was designed to withstand the structural and thermal loads encountered during NASA science missions and to attain performance and lifetime levels consistent with NASA missions. Aerojet and NASA Glenn Research Center have completed the EM thruster design, structural and thermal analysis, fabrication of thruster components, and have assembled and extensively tested one EMl thruster. Performance and thermal characterization of the engineering model thruster has been performed for discharge power levels up to 3.5 kW. The results indicate discharge efficiencies up to of 63% and discharge specific impulse up to 2,930 seconds. In addition to the thruster development, the HiVHAc project is leveraging power processing unit and xenon flow system developments sponsored by other projects but that can apply directly to a HiVHAc system. The goal is to advance the technology readiness level of a HiVHAc propulsion system to 6.

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

[2]  Bruce Pote,et al.  Development of the BPT family of U.S.-designed Hall current thrusters for commercial LEO and GEO applications , 1998 .

[3]  Hani Kamhawi,et al.  Integration Testing of a Modular Discharge Supply for NASA's High Voltage Hall Accelerator Thruster , 2010 .

[4]  David Y. Oh.  Evaluation of Solar Electric Propulsion Technologies for Discovery Class Missions , 2007 .

[5]  Edward Bushway,et al.  Miniature lightweight propellant management assembly for stationary plasma thrusters , 1997 .

[6]  Michael J. Patterson,et al.  NEXT Ion Propulsion System Progress Towards Technology Readiness , 2008 .

[7]  Fred Wilson,et al.  Development Status of the NEXT Propellant Management System , 2004 .

[8]  V. Altuzar,et al.  Atmospheric pollution profiles in Mexico City in two different seasons , 2003 .

[9]  Hani Kamhawi,et al.  Hall Thruster Technology for NASA Science Missions: HiVHAC Status Update , 2007 .

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

[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]  J. Sovey.  In Situ, Time-Resolved Accelerator Grid Erosion Measurements in the NSTAR 8000 Hour Ion Engine Wear Test , 1997 .

[13]  Eric Pencil,et al.  The NASA In-Space Propulsion Technology project's current products and future directions , 2010, 2010 IEEE Aerospace Conference.

[14]  Mariano Andrenucci,et al.  Development of a Telemicroscopy Diagnostic Apparatus and Erosion Modelling in Hall Effect Thrusters , 2009 .

[15]  Hani Kamhawi,et al.  Development Status of the HiVHAC Hall Thruster , 2008 .

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

[17]  Hani Kamhawi,et al.  Advanced Xenon Feed System (AXFS) Development and Hot-fire Testing , 2009 .

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

[19]  E. Turiel.  The Development of Morality , 2007 .

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

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

[22]  T. W. Haag.  Thrust stand for high‐power electric propulsion devices , 1991 .

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

[24]  N. Maslennikov,et al.  SPT-100 subsystem qualification status , 1995 .

[25]  Hani Kamhawi,et al.  Preliminary Performance Characterization of the High Voltage Hall Accelerator Engineering Model Thruster , 2009 .