Theoretical and experimental investigation of Hall thruster miniaturization

Interest in small-scale space propulsion continues to grow with the increasing number of small satellite missions, particularly in the area of formation flight. Miniaturized Hall thrusters have been identified as a candidate for lightweight, high specific impulse propulsion systems that can extend mission lifetime and payload capability. A set of scaling laws was developed that allows the dimensions and operating parameters of a miniaturized Hall thruster to be determined from an existing, technologically mature baseline design. The scaling analysis preserves the dominant plasma processes that determine thruster performance including ionization, electron confinement and recombination losses. These scaling laws were applied to the design of a 9mm diameter, nominally 200W thruster based on the Russian D-55 anode layer Hall thruster. The Miniature Hall Thruster (MHT-9) design was further refined using magnetostatic and steady-state thermal finite element modeling techniques. Performance testing was conducted over a wide range of input powers from 20-500W with voltages between 100-300V and propellant flow rates of 0.3-1.0mg/s. Measured thrust was 1-18mN with a maximum thrust efficiency of 34% and specific impulse of 2000s. Significant erosion of thruster surfaces was observed due to the high plasma density required to maintain collisional mean free paths. Although the thrust efficiency was significantly lower than predicted by scaling laws, the MHT-9 is the best performing subcentimeter diameter Hall thruster built to date. A dimensionless performance analysis has shown that while the magnetic confinement ratio was successfully scaled, the thruster did not maintain the desired Knudsen number because of plasma heating. These trends were confirmed using a computational simulation. An analytical model of electron temperature predicts that, due to a larger relative exposed wall area, the peak temperature inside the MHT-9 is higher than that of the D-55, resulting in greater ion losses and beam divergence. The inability to maintain geometric similarity was a result of the inherent challenges of maintaining magnetic field shape and strength at

[1]  Thomas W. Haag,et al.  Design of a thrust stand for high power electric propulsion devices , 1989 .

[2]  R. Hofer,et al.  Development and characterization of high -efficiency, high -specific impulse xenon Hall thrusters. , 2004 .

[3]  Nicolas Gascon,et al.  Further Development of a Micro Hall Thruster , 2006 .

[4]  Bruce Pote,et al.  Performance of a High Specific Impulse Hall Thruster , 2001 .

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

[6]  Yassir Azziz,et al.  Instrument development and plasma measurements on a 200-watt Hall thruster plume , 2003 .

[7]  T. Haag,et al.  RHETT/EPDM Performance Characterization , 1998 .

[8]  E. Ahedo,et al.  One-dimensional model of the plasma flow in a Hall thruster , 2001 .

[9]  James Joseph Szabo,et al.  Fully kinetic numerical modeling of a plasma thruster , 2001 .

[10]  Mariano Andrenucci,et al.  Development Status of the HT-100 Miniaturized Hall Effect Thruster System , 2005 .

[11]  Robert S. Jankovsky,et al.  High Voltage TAL Performance , 2001 .

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

[13]  Yassir Azziz,et al.  Experimental and theoretical characterization of a Hall thruster plume , 2007 .

[14]  Vladimir Kim,et al.  Development and characterization of small SPT , 1998 .

[15]  Robert S. Jankovsky,et al.  Test Results of a 200 W Class Hall Thruster , 1998 .

[16]  M. Bacal,et al.  Investigation of a small, closed electron drift, stationary plasma thruster , 1996 .

[17]  Yevgeny Raitses,et al.  Parametric investigation of miniaturized cylindrical and annular Hall thrusters , 2001 .

[18]  Vadim Khayms,et al.  Design of a miniaturized Hall thruster for microsatellites , 1996 .

[19]  E. Choueiri Fundamental difference between the two Hall thruster variants , 2001 .

[20]  Mark A. Cappelli,et al.  Transport Physics in Hall Plasma Thrusters , 2002 .

[21]  Jeff Monheiser,et al.  Development and Testing of a Low-Power Hall Thruster System , 2008 .

[22]  Vadim Khayms,et al.  Advanced propulsion for microsatellites , 2000 .

[23]  S. Dubovitsky,et al.  Technology and design of an infrared interferometer for the Terrestrial Planet Finder , 2003 .

[24]  Max J. Schonhuber Breakdown of Gases Below Paschen Minimum: Basic Design Data of High-Voltage Equipment , 1969 .

[25]  A. Kruithof,et al.  Townsend's ionization coefficients for neon, argon, krypton and xenon , 1940 .

[26]  Robert S. Jankovsky,et al.  Multimode, high specific impulse Hall thruster technology , 2000 .

[27]  Murat Celik,et al.  Experimental and computational studies of electric thruster plasma radiation emission , 2007 .

[28]  James E. Polk,et al.  Experimental Evaluation of Russian Anode Layer Thrusters , 1994 .

[29]  Vincent Blateau,et al.  PIC simulation of a ceramic-lined Hall-effect thruster , 2002 .

[30]  Yevgeny Raitses,et al.  PERFORMANCE STUDIES OF MINIATURIZED CYLINDRICAL AND ANNULAR HALL THRUSTERS , 2002 .

[31]  Andrey A. Shagayda,et al.  The Influence of the Magnetic Field Topology on Hall Thruster Performance , 2006 .

[32]  John M. Sankovic,et al.  Operating characteristics of the Russian D-55 thruster with anode layer , 1994 .

[33]  John M. Sankovic,et al.  The BMDO Russian Hall Electric Thruster Technology (RHETT) Program - From laboratory to orbit , 1997 .

[34]  Vladimir Kim,et al.  Investigation of Operation and Characteristics of Small SPT with Discharge Chamber Walls made of Different Ceramics , 2003 .

[35]  J. Dugan,et al.  VOLUME ION PRODUCTION COSTS IN TENUOUS PLASMAS: A GENERAL ATOM THEORY AND DETAILED RESULTS FOR HELIUM, ARGON, AND CESIUM. , 1967 .