STUDY OF POWER LOSS MECHANISMS IN THE BPT-4000 HALL THRUSTER

Aerojet has developed a high performance multi- mode flightweight Hall thruster for orbit raising and stationkeeping on geo-synchrono us satellites. In order to further understand and improve upon the performance of this state of the art Hall thruster and other next generation thrusters being planned, a detailed study of the power loss mechanisms has been conducted. Calculations of each loss mechanism have been performed using experimental data as input. A comparison of the relative magnitude of each loss mechanism shows that power deposition in the anode and radial kinetic power of the exhaust are the dominant losses in this thruster followed by power deposition in the insulator rings. The calculations also show that the propellant utilization efficiency is only 70% but the voltage losses are minimal. These results indicate potential for improved performance of this and other next generation thrusters if the electron-neutral collision frequency can be increased and the ion beam acceleration focused with improved magnetic field and anode designs.

[1]  A. Gallimore,et al.  Ion energy diagnostics in the plume of an SPT-100 from thrust axis to backflow region , 1998 .

[2]  Alec D. Gallimore,et al.  Near-Field Ion Energy and Species Measurements of a 5-kW Hall Thruster , 2001 .

[3]  R. Dressler,et al.  Ion Dynamics in Hall Effect and Ion Thrusters: Xe' + Xe Symmetric Charge , 2000 .

[4]  Ioannis G. Mikellides,et al.  A Hall effect thruster plume model including large-angle elastic scattering , 2001 .

[5]  Alfred C. Wilson,et al.  The Development and Qualification of a 4.5 kW Hall Thruster Propulsion System for GEO Satellite Applications , 2001 .

[6]  Roger M. Myers,et al.  Launch vehicle and power level impacts on electric GEO insertion , 1996 .

[7]  A. Gallimore,et al.  An investigation of internal ion number density and electron temperature profiles in a laboratory-model Hall thruster , 2000 .

[8]  E. Beiting,et al.  Ion Energy, Ion Velocity and Thrust Vector Measurements for the SPT-140 Hall Thruster , 2000 .

[9]  Alec D. Gallimore,et al.  Very-Near-Field Plume Investigation of the Anode Layer Thruster , 2000 .

[10]  Roger M. Myers,et al.  Advanced Propulsion for Geostationary Orbit Insertion and North-South Station Keeping , 1997 .

[11]  Timothy R. Sarver-Verhey.  Continuing life test of a xenon hollow cathode for a space plasma contactor , 1994 .

[12]  David Q. King,et al.  Multi-mode Hall Thruster Development , 2001 .

[13]  Lee S. Mason,et al.  1000 Hours of Testing on a 10 Kilowatt Hall Effect Thruster , 2001 .

[14]  Timothy R. Sarver-Verhey.  Extended test of a xenon hollow cathode for a space plasma contactor , 1994 .

[15]  A. M. Bishaev,et al.  Local plasma properties in a Hall-current accelerator with an extended acceleration zone , 1978 .

[16]  D. A. King,et al.  Ion flux, energy, and charge-state measurements for the BPT-4000 Hall thruster , 2001 .

[17]  Jack Fisher,et al.  The Qualification of a 4.5 kW Hall Thruster Propulsion Subsystem , 2003 .

[18]  P. Turchi,et al.  A first-principles model for orificed hollow cathode operation , 1992 .

[19]  David H. Manzella.  Stationary Plasma Thruster Plume Emissions , 1994 .

[20]  A. Salhi.  Theoretical and experimental studies of orificed, hollow cathode operation / , 1993 .

[21]  John R. Brophy,et al.  Performance Evaluation and Life Testing of the SPT-100 , 1993 .