Numerical study of a Double Stage Hall Effect Thruster
|
|
- Natalie Gilmore
- 6 years ago
- Views:
Transcription
1 Numerical study of a Double Stage Hall Effect Thruster IEPC--1 Presented at the 9 th International Electric Propulsion Conference, Princeton University, October 1 November, C. Boniface *, G.J.M Hagelaar, L. Garrigues and J.P. Boeuf CPAT, UMR, Université Pau Sbatier, 11 Route de Narbonne, 1 Toulouse Cedex, France M. Prioul ** Snecma Moteurs DPES Site de Villaroche Nord BP9F Moissy-Cramayel, France Abstract: Hall Effect Thrusters (HETs) are ion sources used for satellite station keeping and orbit raising. In Single Stage HETs, the same electric field controls both electron heating and ion acceleration. We present simulations of a new HET concept where ionization and acceleration are separated in two different stages. The ionization chamber is based on an original plasma trap called Galatheas. This Double Stage HET allows more versatile operation and a separate control of thrust and specific impulse. * PhD. Student, CPAT, boniface@cpat.ups-tlse.fr. Research scientist, CPAT, hagelaar@cpat.ups-tlse.fr. Research scientist, CPAT, garrigues@cpat.ups-tlse.fr. Senior research scientist, CPAT, jpb@cpat.ups-tlse.fr. ** Propulsion engineer, Snecma Moteurs, mathieu.prioul@snecma.fr. 1 The 9 th International Electric Propulsion Conference, Princeton University, October 1 November,
2 I. Introduction Hall Effect Thrusters (HETs) are gridless ion engines where a magnetic field barrier is used to slow down the electron conductivity and generate a large electric field that provides collisionless ion acceleration 1. The specific impulse of HETs is in the range 1- s (i.e. the velocity of ejected xenon ions is on the order of 1- km/s) and the thrust to power ratio is about mn/kw. The thrust and the specific impulse of standard Single Stage HETs (SSHETs) are well adapted to the missions of orbit correction and station keeping, but cannot be easily varied and optimized independently, because the same electric field controls both electron heating and ion acceleration. The next generation of satellites however demands flexible multimode thrusters able to provide high thrust for orbit raising or transfer, and high specific impulse for satellite station keeping. High thrust with high mass flow rate and low voltage reduces the duration of orbit transfers, while high specific impulse with high voltage and low mass flow rate is needed to minimize gas consumption during station keeping. An alternative concept of standard HETs consists of separating the two main functions of a Hall Effect thruster where ionization and acceleration are performed in different stages. For instance, Linear Gridless Ion Thruster (LGIT), based on the magnetic confinement of the plasma, are able to increase the residence time of the electrons and so the ionization of the neutral flux. The main problem of the LGIT is the difficulty to ensure a good control of the ion trajectory in order to extract them properly from the ionization stage into the acceleration stage. A new HET concept in which ionization and ion acceleration are controlled independently has been recently proposed -. This Double Stage HET (DSHET) uses a separate chamber to ionize the gas flow, while the ion acceleration is provided by the electric field generated in a magnetic field barrier, as in standard SSHETs. The ionization stage and the classical acceleration stage are shown in the diagram of Fig. 1. The plasma in the ionization stage is confined by a semi Galathea trap generated by a special arrangement of coils and magnetic circuit. By imposing appropriate voltage drops between the myxina coil, the separatrix magnetic field line, and the metallic chamber wall (see Fig. 1), a potential well is created that confines the ions and guides them to the entrance of the channel, where they are subsequently extracted and ejected. The minimum potential in the ionization chamber is along the separatrix line, and is close to the potential of the anode of the acceleration stage. The maximum potential ( to V above the latter) is along the myxina and the chamber wall. In such a configuration, the magnetic field lines tend to be equipotential in first approximation. Electrons coming from the channel into the ionization chamber are confined along the magnetic field lines and then drift slowly, across the magnetic field lines, towards the myxina and chamber wall due to collisions with neutral atoms. Figure 1. Schematic of the DSHET showing the ionization and acceleration stages. The intermediate electrode serves as the anode of the acceleration stage and the cathode of the ionization stage, where it is intercepted by the separatrix magnetic field line. The 9 th International Electric Propulsion Conference, Princeton University, October 1 November,
3 A quasineutral hybrid model, similar to the one described in Ref., has been adapted to the DSHET of Fig. 1. In this model, the ions and neutral atoms are described with a Particle-In-Cell simulation. The electric field is deduced from the electron momentum equation (generalized Ohms law) and current conservation. The electron energy and ionization rate can be calculated either from fluid equations assuming a maxwellian electron energy distribution, or from a Monte-Carlo simulation of the electron trajectories. The results shown in Fig. have been obtained with the Monte Carlo treatment of the electrons. Figure : (a,top) Calculated ionization rate (log scale over decades, from yellow to red, maximum 1 m - s -1 ) and examples of ion trajectories; (a,bottom) positions of a sample of ions in the simulation; (b) potential distribution inside the thruster (only part of the channel is represented). Conditions: xenon mass flow rate. mg/s, applied voltage in the acceleration channel V, applied voltage in the ionization chamber V. We see in Fig. (a, bottom part) the trapping of ions in the potential well (b) in the ionization chamber and their extraction and acceleration (a, top) in the channel. II. Ionization processes in DSHET We focus now on the study of the first chamber of the DSHET as an ion source. The aim of this study is to help to better understand the electron multiplication in such complex magnetic configuration as well as the spatial distribution of ionisation in the chamber. We used a Monte-Carlo simulation of electrons based on the null-collision method 9 in order to have an accurate description of collisionnal processes. In these simulations, the magnetic and the electric fields and the mass flow rate are given. The magnetic field B, obtained by using the FEMM software 1, exhibits a complex structure where its intensity is larger near the internal wall than the external wall. There also is a point of zero B-field near the entrance of the ionization chamber. The potentiel well and the mass flow rate are respectively V(cf. fig. b) and.mg/s. Neutral gas is injected near the external wall. We inject at the entrance of the chamber an electron flux according to a maxwellian distribution at a given electron temperature T e. We simulate each electron for 1 - s (physical time) which is much longer than the time scale for ionisation, excitation and elastic collisions, after that the electrons are ejected from the simulation. Moreover, we suppose that reflexion with walls are specular. We simulate one thousand primary electrons and the secondary electrons created by ionization in order to have good statistics. The simulation time is four hours with a GHz PC. The 9 th International Electric Propulsion Conference, Princeton University, October 1 November,
4 A. Maxwellian electron distribution at T e =1 ev In the first case, we inject a maxwellian electron distribution at T e =1eV. For a V potentiel well, we obtain 9 secondary electrons created for 1 primary electrons, so an electron multiplication near to. Fig. shows the rate of collisionnal processes and the mean electron energy in the chamber. a) b) E E.9E1.E1 1.E1 E E.9E19.E19 1.E19 E1 c) d) Figure. Collisionnal processes in the ionization chamber: a) Ionization source term, log. scale over decades (m - s -1 ), white color where < 1 1 m - s -1 ; b) Excitation source term (m - s -1 ), log. scale over decades; c) Elastic collisions source term (m - s -1 ); log. scale over decades, from blue to red, maximum 1 1 m - s -1 ; Electron mean energy (ev), log. scale over 1 decade. a) and b) at the same scale. We can see a strongly non-uniform distribution of ionization in the chamber. The maximum (.1 m - s -1 ) is at the top of the well near the external wall and the myxina whereas ionization is very weak around the separatrix. This distribution is strongly influenced by the magnetic topology and the neutral gas injection. Indeed, the electron transport across the magnetic field lines is easier in weak magnetic field and high neutral density regions. The electrons are initially trapped on the separatrix where they do not have enough energy for inelastic collisions. When the electrons drift towards the chamber wall and the myxina, they gain energy and start exciting and ionizing the neutral gas particles. The total electron multiplication however is weak and the ionization distribution strongly nonuniform. B. Maxwellian electron distribution at T e =1 ev In this case, we inject a maxwellian electron distribution at T e =1eV. We obtain an electron multiplication of -. Fig. shows the ionization source term and the electron mean energy. The 9 th International Electric Propulsion Conference, Princeton University, October 1 November,
5 a) 1 E.E 1.1E E1.E1 1.1E1 E.E 1.1E E19.E19 1.1E19 E1 b) Figure. a) Ionization source term, log. scale over decades (m - s -1 ); b) Electron mean energy (ev), log. scale over 1 decade. We note a major difference in the spatial distribution of the ionization in the two cases. Firstly, we have an important ionization around the separatrix. In the middle of the well, the ionization and excitation rates are about equaled. Finally at the top of the well, there is a strong ionization with electron mean energy near to - ev. Indeed, the initial electron energy at the entrance of the channel allows them to ionize quickly (mean ionization time 1-9 s against 1 - s at T e =1eV) so that it limits the influence of electron energy losses by excitation processes. Concerning the difference between internal and external walls, this is always due to the magnetic topology. All in all, one condition appears clearly: the initial energy of primary electrons at the entrance of the chamber wall controls strongly the ionization in the chamber of DSHET. Electrons are more influenced by their initial energy than by potential well. Of course, the magnetic field is still important in so far as the confinement allows to increase the electron residence time. Besides the potential well is essential to trap ions as we have seen in Fig. III. Ion extraction in DSHETs The goal of this study is to describe qualitatively the influence of the magnetic field configuration on the extraction process. In such a configuration, the magnetic field lines tend to be equipotential in a first approximation. We used the Monte-Carlo simulation of the electrons to calculate accurately the ionization source term distribution. Then this distribution is injected in the hybrid model to deduce the neutral density and the electric potential profiles. We repeat the process in order to reach a steady state. In the acceleration channel, we inject the primary electrons following a maxwellian distribution at T e =1eV according to the calculation of the previous section ( cf. Fig. ). A. Magnetic field modeling We use the Finite Element Method Magnetic (FEMM) solver to calculate the magnetic field distribution for a given arrangement of the magnetic circuit and a given value for the coil currents. Different values of current myxina coil have been designed to generate different magnetic field configurations. The magnetic field lines are plotted in Fig. for three different topologies varying only the current in the myxina coil. We also represent the axial The 9 th International Electric Propulsion Conference, Princeton University, October 1 November,
6 variations of the calculated radial magnetic field strength along the median line (radial position. cm) between the channel walls for the different magnetic field configurations. The current of the myxina coil increases from the case 1 to the case. Modifying the current on the myxina coil changes the axial position of the zero B-field. The consequences are a strong modification of the magnetic field lines in the ionization chamber, especially the curvature of the lines near the entrance of the ionization chamber, and the magnetic field gradient in the acceleration channel. 1 1 Case 1 Case Case Zero B-field 1 1 MAGNETIC FIELD (U.A.) (A.U) Case 1 Case Case Figure. DSHET magnetic field lines calculated with FEMM for three different values of the myxina coil currents (case 1, and ). The separatrix is in green color. Axial variations of the calculated radial magnetic field strength along the median line between the channel walls for different magnetic configurations. C. Ion extraction The spatial ion distribution plotted Fig. give information on the shape of the ion beam, especially in the region situated between the zero B-field and the entrance of the channel. This region is a transition between the ionization chamber and the acceleration channel. The ion distributions in the (x,r) plane are represented in Fig. for the three different topologies of Fig.. We also represent the axial variations of the calculated electric potential along the median line (radial position. cm) between the channel walls for the different magnetic field configurations (cf. Fig. ). The 9 th International Electric Propulsion Conference, Princeton University, October 1 November,
7 9 1 Case Ion impact 1 1 Case 9 1 POTENTIAL (V) 1 1 Chamber 1 Case 1 Case Case V Ion impact Case Transition zone x=cm Channel Figure : Ion distribution in the (x,r) plane for the three different magnetic configurations. Axial variations of the calculated electric potential along the median line between the channel walls for different magnetic field configurations. As we discussed in the section III.B, we vary the coil current in the myxina for the three different magnetic configurations. Increasing the coil current in the myxina from case 1, case to case shifts the axial position of the zero-b field near the acceleration channel and so the shape of the magnetic field lines in the ionization chamber as we have shown on Fig.. Case 1 features a wider ion beam in the region of the transition than case. This is due mainly to the shape of the magnetic field lines intercepting the oblique wall in this region; many ions hit the oblique wall and so they can recombine to the channel wall leading to a re-ionization in the channel. Case exhibits magnetic field lines practically tangent to the wall which guide the ions correctly from the ionization chamber to the entrance of the acceleration channel. However, in case the position of the zero B-field is closer to the channel than in case 1, and the electric potential drops further in the channel as we can see in Fig.. Therefore, many ions have no time to convert their transversal velocity into longitudinal velocity, and hit the channel wall where they recombine into neutrals. The magnetic configuration of case is a compromise between cases 1 and in order to have a better extraction. All in all, the ion extraction process is influenced by both the shape of the magnetic field lines near the transition region (to guide the ions correctly) and the position of the electric field (to correctly convert the transverse velocity into longitudinal velocity). It is possible to control these two features by varying the axial position of the zero B-field. IV. Conclusion These preliminary simulation results present some features of the DSHET in qualitative agreement with the experiments. More work is needed to better understand its possibilities and limits, and to optimize the ion extraction from the ionization chamber. An important issue concerning the ionization stage is the spatial distribution of ionization which is influenced by the magnetic topology. The electron multiplication and so the ionization efficiency are controlled mainly by the maximum electron mean energy (initial kinetic energy and potential energy) that electrons can obtain in the chamber. In the future, it could be interesting to have an experimental estimate of initial energy at chamber entrance, although this is linked to anomalous electron transport occurring in the acceleration channel11. The 9th International Electric Propulsion Conference, Princeton University, October 1 November,
8 The magnetic configuration in the ionization chamber controls the shape of the magnetic field lines in the chamber and the magnetic field gradient in the channel which strongly influences the ion extraction process. Nonetheless, more work is needed to better understand the different processes in the DSHET, notably by improving the calculation of the electric potential inside the ionization chamber where magnetic field is locally weak and neutral density is locally high. This study is under way. Acknowledgments This study has been performed in the framework of GDR CNRS/CNES/SNECMA n 9 Propulsion Spatiale à Plasma. We want to acknowledge too the support from European Space agency (ESA). The authors would like to thank E. Chesta and E. Gengembre for helpful discussions. Discussions with A.I. Morozov, A. Bugrova and V.V. Savel ev on the DSHET concept are also gratefully acknowledged. References 1 V. V. Zhurin, H. R. Kaufmann and R. S. Robinson, "Physics of closed drift thrusters", Plasma Sources Sci. Technol., R1- R P.Y. Peterson and A.D. Gallimore, The Performance and Plume Characterization of a Laboratory Gridless Ion Thruster with Closed Electron Drift Acceleration, th AIAA Joint Propulsion Conference and Exhibit, July 11-1, Fort Lauderdale, FL, paper AIAA--9. SNECMA Patent, 9 July. E. Chesta et al., "Flexible variable-specific impulse electric propulsion systems for planetary missions", th International conference on Low-Cost planetary missions, ESTEC, - September, ESA SP-. M. Prioul et al., "Development of a Double Stage Hall Effect Thruster", th International Spacecraft Propulsion Conference, Sardinia, June. A.I. Morozov and V.V. Savel ev, "On Galateas magnetic traps with plasma-embedded conductors", Physics Uspekhi 1, 19-19, 199. G.J.M. Hagelaar, J. Bareilles, L. Garrigues and J.P. Boeuf, "Two-dimensional model of a stationary plasma thruster", J. Appl. Phys. 91, 9-9,. C. Boniface, G.J.M. Hagelaar, L. Garrigues, J.P. Boeuf and M. Prioul "Modeling of Double Stage Hall Effect Thruster IEEE. Trans. Plasma Sci. (), (). 9 Jean-Pierre Boeuf, PhD thesis. 1 FEMM 11 G.J.M. Hagelaar, J. Bareilles, L. Garrigues and J.P. Boeuf, "Role of anomalous electron transport in a stationary plasma thruster simulation", J. Appl. Phys. 9,,. The 9 th International Electric Propulsion Conference, Princeton University, October 1 November,
Model analysis of a double stage Hall effect thruster with double-peaked magnetic field and intermediate electrode
Model analysis of a double stage Hall effect thruster with double-peaked magnetic field and intermediate electrode IEPC-2007-121 Presented at the 30 th International Electric Propulsion Conference, Florence,
More informationRESEARCH ON TWO-STAGE ENGINE SPT-MAG
RESEARCH ON TWO-STAGE ENGINE SPT-MAG A.I. Morozov a, A.I. Bugrova b, A.D. Desiatskov b, V.K. Kharchevnikov b, M. Prioul c, L. Jolivet d a Kurchatov s Russia Research Center, Moscow, Russia 123098 b Moscow
More informationPARAMETRIC STUDY OF HALL THRUSTER OPERATION BASED ON A 2D HYBRID MODEL : INFLUENCE OF THE MAGNETIC FIELD ON THE THRUSTER PERFORMANCE AND LIFETIME
PARAMETRIC STUDY OF HALL THRUSTER OPERATION BASED ON A D HYBRID MODEL : INFLUENCE OF THE MAGNETIC FIELD ON THE THRUSTER PERFORMANCE AND LIFETIME L. Garrigues, C. Boniface, J. Bareilles, G.J.M. Hagelaar,
More informationTwo Dimensional Hybrid Model of a Miniaturized Cylindrical Hall Thruster
Two Dimensional Hybrid Model of a Miniaturized Cylindrical Hall Thruster IEPC-2007-157 Presented at the 30 th International Electric Propulsion Conference, Florence, Italy L. Garrigues *, G. J. M. Hagelaar,
More informationPlasma Properties Inside a Small Hall Effect Thruster
Plasma Properties Inside a Small Hall Effect Thruster IEPC-2013-415 Presented at the 33 rd International Electric Propulsion Conference, The George Washington University, Washington, D.C., USA Maziar Dabiri
More informationModélisation de sources plasma froid magnétisé
Modélisation de sources plasma froid magnétisé Gerjan Hagelaar Groupe de Recherche Energétique, Plasma & Hors Equilibre (GREPHE) Laboratoire Plasma et Conversion d Énergie (LAPLACE) Université Paul Sabatier,
More informationBeams and magnetized plasmas
Beams and magnetized plasmas 1 Jean-Pierre BOEUF LAboratoire PLAsma et Conversion d Energie LAPLACE/ CNRS, Université Paul SABATIER, TOULOUSE Beams and magnetized plasmas 2 Outline Ion acceleration and
More informationThe electron diffusion into the channel of stationary plasma thruster
The electron diffusion into the channel of stationary plasma thruster IEPC-215-397 Presented at Joint Conference of 3th International Symposium on Space Technology and Science 34th International Electric
More informationDownscaling a HEMPT to micro-newton Thrust levels: current status and latest results
Downscaling a HEMPT to micro-newton Thrust levels: current status and latest results IEPC-2015-377/ISTS-2015-b-377 Presented at Joint Conference of 30th International Symposium on Space Technology and
More informationOne dimensional hybrid Maxwell-Boltzmann model of shearth evolution
Technical collection One dimensional hybrid Maxwell-Boltzmann model of shearth evolution 27 - Conferences publications P. Sarrailh L. Garrigues G. J. M. Hagelaar J. P. Boeuf G. Sandolache S. Rowe B. Jusselin
More informationHigh-frequency Instabilities in Hall-effect Thrusters: Correlation with the Discharge Current and Thruster Scale Impact
High-frequency Instabilities in Hall-effect Thrusters: Correlation with the Discharge Current and Thruster Scale Impact IEPC-5- Presented at the 9 th International Electric Propulsion Conference, Princeton
More informationExperimental Investigation of Magnetic Field Topology Influence on Structure of Accelerating Layer and Performance of Hall Thruster
Experimental Investigation of Magnetic Field Topology Influence on Structure of Accelerating Layer and Performance of Hall Thruster IEPC-005-033 Presented at the 9 th International Electric Propulsion
More informationPhysics and Modelling of a Negative Ion Source Prototype for the ITER Neutral Beam Injection
1 ITR/P1-37 Physics and Modelling of a Negative Ion Source Prototype for the ITER Neutral Beam Injection J.P. Boeuf a, G. Fubiani a, G. Hagelaar a, N. Kohen a, L. Pitchford a, P. Sarrailh a, and A. Simonin
More informationComparison of SPT and HEMP thruster concepts from kinetic simulations
Comparison of SPT and HEMP thruster concepts from kinetic simulations IEPC-2009-159 Presented at the 31st International Electric Propulsion Conference, University of Michigan Ann Arbor, Michigan USA K.
More informationPlaS-40 Development Status: New Results
PlaS-40 Development Status: New Results IEPC-2015-99/ISTS-2015-b-9 Presented at Joint Conference of 30 th International Symposium on Space Technology and Science 34 th International Electric Propulsion
More informationDevelopment of a Hall Thruster Fully Kinetic Simulation Model Using Artificial Electron Mass
Development of a Hall Thruster Fully Kinetic Simulation Model Using Artificial Electron Mass IEPC-013-178 Presented at the 33rd International Electric Propulsion Conference, The George Washington University
More informationKinetic simulation of the stationary HEMP thruster including the near field plume region
Kinetic simulation of the stationary HEMP thruster including the near field plume region IEPC-2009-110 Presented at the 31st International Electric Propulsion Conference, University of Michigan Ann Arbor,
More informationTwo-dimensional Particle-In-Cell model of the extraction region of the PEGASES ion-ion plasma source
Two-dimensional Particle-In-Cell model of the extraction region of the PEGASES ion-ion plasma source IEPC-2013-249 Presented at the 33rdInternational Electric Propulsion Conference, The George Washington
More informationOVERVIEW OF ASTRIUM MODELLING TOOL FOR PLASMIC THRUSTER FLOW FIELD SIMULATION C.
1 OVERVIEW OF ASTRIUM MODELLING TOOL FOR PLASMIC THRUSTER FLOW FIELD SIMULATION C. Theroude, S. Provost, P. Chèoux-Damas Astrium SAS, 31 avenue des Cosmonautes, 31402 Toulouse Cedex 4 (France) Phone :
More informationAssessment of fluctuation-induced and wall-induced anomalous electron transport in HET
Assessment of fluctuation-induced and wall-induced anomalous electron transport in HET IEPC-2015-418 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International
More informationPlasma Formation in the Near Anode Region in Hall Thrusters
41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 10-13 July 2005, Tucson, Arizona AIAA 2005-4059 41 st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit AIAA-2005-4059 Plasma Formation
More informationAbstract. Objectives. Theory
A Proposal to Develop a Two-Stage Gridless Ion Thruster with Closed Electron Drift Richard R. Hofer Plasmadynamics and Electric Propulsion Laboratory (PEPL) Department of Aerospace Engineering University
More informationDevelopment and qualification of Hall thruster KM-60 and the flow control unit
Development and qualification of Hall thruster KM-60 and the flow control unit IEPC-2013-055 Presented at the 33rd International Electric Propulsion Conference, The George Washington University Washington,
More informationAn advanced simulation code for Hall effect thrusters
An advanced simulation code for Hall effect thrusters P. Fajardo, M. Merino, E. Ahedo pablo.fajardo@uc3m.es EPIC Workshop October 2017, Madrid Contents Plasmas and Space propulsion Team (EP2-UC3M) CHEOPS
More informationImprovement of Propulsion Performance by Gas Injection and External Magnetic Field in Electrodeless Plasma Thrusters
Improvement of Propulsion Performance by Gas Injection and External Magnetic Field in Electrodeless Plasma Thrusters IEPC-217-249 Presented at the th International Electric Propulsion Conference Georgia
More informationHall Thruster Electron Mobility Investigation using Full 3D Monte Carlo Trajectory Simulations
Hall Thruster Electron Mobility Investigation using Full 3D Monte Carlo Trajectory Simulations IEPC-2007-291 Presented at the 30 th International Electric Propulsion Conference, Florence, Italy Darren
More informationFigure 1, Schematic Illustrating the Physics of Operation of a Single-Stage Hall 4
A Proposal to Develop a Double-Stage Hall Thruster for Increased Efficiencies at Low Specific-Impulses Peter Y. Peterson Plasmadynamics and Electric Propulsion Laboratory (PEPL) Aerospace Engineering The
More informationWall Erosion in 2D Hall Thruster Simulations
42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 9-12 July 2006, Sacramento, California AIAA 2006-4656 Wall Erosion in 2D Hall Thruster Simulations Emmanuelle Sommier *, Michelle K. Allis,
More informationGradient drift instability in Hall plasma devices
Gradient drift instability in Hall plasma devices IEPC-3-75 Presented at the 33 rd International Electric Propulsion Conference, The George Washington University, Washington, D.C., USA October 6, 3 W.Frias
More informationSelf consistent kinetic simulations of SPT and HEMP thrusters including the near-field plume region
Self consistent kinetic simulations of SPT and HEMP thrusters including the near-field plume region K. Matyash 1, R. Schneider, A. Mutzke, O. Kalentev Max-Planck-Institut für Plasmaphysik, EURATOM Association,
More informationMultiple Thruster Propulsion Systems Integration Study. Rusakol, A.V..Kocherpin A.V..Semenkm A.V.. Tverdokhlebov S.O. Garkusha V.I.
IEPC-97-130 826 Multiple Thruster Propulsion Systems Integration Study Rusakol, A.V..Kocherpin A.V..Semenkm A.V.. Tverdokhlebov S.O. Garkusha V.I. Central Research Institute of Machine Building (TsNIIMASH)
More informationKinetic simulations of SPT and HEMP thrusters including the near-field plume region
This work was presented at 21st International Conference on Numerical Simulation of Plasmas (ICNSP'09) 1 Kinetic simulations of SPT and HEMP thrusters including the near-field plume region K. Matyash,
More informationComparison of SPT and HEMP thruster concepts from kinetic simulations
Comparison of SPT and HEMP thruster concepts from kinetic simulations K. Matyash, R. Schneider, A. Mutzke, O. Kalentev Max-Planck-Institut für Plasmaphysik, EURATOM Association, Greifswald, D-1749, Germany
More informationOptimization of the design of a wall-less Hall thruster
Optimization of the design of a wall-less Hall thruster IEPC-2015-182 /ISTS-2015-b-182 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International Electric
More informationThe classical model of a Hall thruster is based on electron conduction across magnetic field lines being
Self-Consistent Calculation of Electron Transport in a Cylindrical Hall Thruster Lubos Brieda, Michael Keidar The George Washington University, Washington, D.C. 20052 Yevgeny Raitses and Nathaniel J. Fisch
More informationEffects of the Gas Pressure on Low Frequency Oscillations in E B Discharges
Effects of the Gas Pressure on Low Frequency Oscillations in E B Discharges IEPC-2015-307 /ISTS-2015-b-307 Presented at Joint Conference of 30th International Symposium on Space Technology and Science
More informationFor a given mass flow ṁ and thrust F, we would like to minimize the running power P. Define a thruster efficiency, P = I a V a (2) V a
Session : Hall Thruster Efficiency For a given mass flow ṁ and thrust F, we would like to minimize the running power P. Define a thruster efficiency, F 2 η = (1) 2ṁP where F 2 /2ṁ is the minimum required
More informationDevelopment of stationary plasma thruster SPT-230 with discharge power of kw
Development of stationary plasma thruster SPT-230 with discharge power of 10...15 kw IEPC-2017-548 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology Atlanta,
More informationOPERATION PECULIARITIES OF HALL THRUSTER WITH POWER kw AT HIGH DISCHARGE VOLTAGES
OPERATION PECULIARITIES OF HALL THRUSTER WITH POWER 1.5 2.0 kw AT HIGH DISCHARGE VOLTAGES M.B. Belikov, N.V. Blinov, O.A. Gorshkov, R.N. Rizakhanov, A.A. Shagayda Keldysh Research Center 125438, Moscow,
More informationKINETIC DESCRIPTION OF MAGNETIZED TECHNOLOGICAL PLASMAS
KINETIC DESCRIPTION OF MAGNETIZED TECHNOLOGICAL PLASMAS Ralf Peter Brinkmann, Dennis Krüger Fakultät für Elektrotechnik und Informationstechnik Lehrstuhl für Theoretische Elektrotechnik Magnetized low
More informationParticle-in-Cell Simulations for a variable magnet length Cusped-Field thruster
Particle-in-Cell Simulations for a variable magnet length Cusped-Field thruster IEPC-213-171 Presented at the 33rd International Electric Propulsion Conference, The George Washington University Washington,
More informationWall-induced Cross-field Electron Transport with Oblique Magnetic Field Lines
Wall-induced Cross-field Electron Transport with Oblique Magnetic Field Lines IEPC-213-77 Presented at the 33 rd International Electric Propulsion Conference, The George Washington University, Washington,
More informationA COMPUTATIONAL STUDY OF SINGLE AND DOUBLE STAGE HALL THRUSTERS
A COMPUTATIONAL STUDY OF SINGLE AND DOUBLE STAGE HALL THRUSTERS Kay Sullivan, Manuel Martínez-Sánchez, Oleg Batishchev and James Szabo Massachusetts Institue of Technology 77 Massachusetts Avenue Cambridge,
More informationEP2Plus: a hybrid plasma. plume/spacecraft. interaction code. F. Cichocki, M. Merino, E. Ahedo
EP2Plus: a hybrid plasma plume/spacecraft interaction code F. Cichocki, M. Merino, E. Ahedo 24 th SPINE meeting ESTEC, Noordwijk, October 23 rd, 2017 Contents Introduction to EP2PLUS Overall structure
More informationDevelopment of a Two-axis Dual Pendulum Thrust Stand for Thrust Vector Measurement of Hall Thrusters
Development of a Two-axis Dual Pendulum Thrust Stand for Thrust Vector Measurement of Hall Thrusters Naoki Nagao, Shigeru Yokota, Kimiya Komurasaki, and Yoshihiro Arakawa The University of Tokyo, Tokyo,
More informationA Hydrodynamic-Based Erosion Model for Hall Thrusters
A Hydrodynamic-Based Erosion Model for Hall Thrusters IEPC-2005-013 Presented at the 29 th International Electric Propulsion Conference, Princeton University John T. Yim, Michael Keidar, and Iain D. Boyd
More informationarxiv: v1 [physics.plasm-ph] 16 May 2018
Two-dimensional Modeling of the Hall Thruster Discharge with Non-uniform Propellant Supply in Azimuth Rei Kawashima a,, Junhwi Bak a, Kimiya Komurasaki a, Hiroyuki Koizumi b a Department of Aeronautics
More informationMIREA. Moscow, Russia
2245 IEPC-93-247 MAIN FEATURES OF PHYSICAL PROCESSES IN STATIONARY PLASMA THRUSTERS A.I. Bugrova, A.V. Desiatskov, V.K. Kharchevnikov, A.I. Morozov Abstract MIREA Moscow, Russia Introduction The paper
More informationIon velocity evolution with channel width, magnetic topology and propellant in a 200 W Hall thruster
Ion velocity evolution with channel width, magnetic topology and propellant in a 200 W Hall thruster IEPC-2011-123 Presented at the 32 nd International Electric Propulsion Conference, Wiesbaden, Germany
More informationSome results of the small power SPT models creation
IEPC-97-151 931 Some results of the small power SPT models creation Aidar B. Jakupov, Sergey A. Khartov, A&met M. Yakubov Moscow State Aviation Institute (MAI) Department Spacecraft Electric Propulsion
More informationExperimental Investigations of a Krypton Stationary Plasma Thruster
Experimental Investigations of a Krypton Stationary Plasma Thruster A. I. Bugrova, A.M. Bishaev, A. V. Desyatskov, M.V. Kozintseva, A. S. Lipatov, M. Dudeck To cite this version: A. I. Bugrova, A.M. Bishaev,
More informationDevelopment of Micro-Vacuum Arc Thruster with Extended Lifetime
Development of Micro-Vacuum Arc Thruster with Extended Lifetime IEPC-9-9 Presented at the st International Electric Propulsion Conference, University of Michigan Ann Arbor, Michigan USA September, 9 TaiSen
More informationModeling nonthermal plasmas generated in glow discharges*
Pure Appl. Chem., Vol. 71, No. 10, pp. 1837±1844, 1999. Printed in Great Britain. q 1999 IUPAC Modeling nonthermal plasmas generated in glow discharges* I. Revel, Ph. Belenguer, J. P. Boeuf and L. C. Pitchford²
More informationParticle Simulation of Hall Thruster Plumes in the 12V Vacuum Chamber
Particle Simulation of Hall Thruster Plumes in the 12V Vacuum Chamber IEPC-2005-138 Presented at the 29 th International Electric Propulsion Conference, Princeton University, Iain D. Boyd 1, Quanhua Sun
More informationHall Thruster Modifications for Reduced Power Operation
Hall Thruster Modifications for Reduced Power Operation IEPC-2005-080 Presented at the 29 th International Electric Propulsion Conference, Princeton University, October 31 November 4, 2005 J. Ashkenazy
More informationExperimental study of a high specific impulse plasma thruster PlaS-120
Experimental study of a high specific impulse plasma thruster PlaS-120 IEPC-2015-154 /ISTS-2015-b-154 Presented at Joint Conference of 30 th International Symposium on Space Technology and Science 34 th
More informationNew electric propulsion technologies investigation by simulation
New electric propulsion technologies investigation by simulation Mario Merino Equipo de Propulsión Espacial por Plasmas (EP2) Universidad Politécnica de Madrid (UPM) Contents The EP2 group and their activities
More informationPPS 1350-G Performance assessment with permanent magnets
PPS 1350-G Performance assessment with permanent magnets IEPC-2011-119 Presented at the 32nd International Electric Propulsion Conference, Wiesbaden Germany V. Vial *, L. Godard and N. Cornu Snecma, Safran
More informationHigh-impulse SPT-100D thruster with discharge power of kw
High-impulse SPT-D thruster with discharge power of 1.0 3.0 kw IEPC-2017-40 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology Atlanta, Georgia USA R. Gnizdor
More informationMeasurement of Anode Current Density Distribution in a Cusped Field Thruster
Measurement of Anode Current Density Distribution in a Cusped Field Thruster IEPC-2015-375 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International
More informationKinetic Simulation of Effects of Secondary Electron Emission on Electron Temperature in Hall Thrusters
Kinetic Simulation of Effects of Secondary Electron Emission on Electron Temperature in Hall Thrusters IEPC-25-78 Presented at the 29 th International Electric Propulsion Conference, Princeton University
More informationPlasma Energy Conversion in the Expanding Magnetic Nozzle
Plasma Energy Conversion in the Expanding Magnetic Nozzle IEPC-2015-355/ISTS-2015-b-355 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International
More informationResistive Instabilities in a Hall Thruster Under the Presence of Collisions and Thermal Motion of Electrons
16 The Open Plasma Physics Journal 011 4 16-3 Open Access Resistive Instabilities in a Hall Thruster Under the Presence of Collisions and Thermal Motion of Electrons Sukhmander Singh and Hitendra K. Malik
More informationOperation Characteristics of Diverging Magnetic Field Electrostatic Thruster
Operation Characteristics of Diverging Magnetic Field Electrostatic Thruster IEPC-07-9 Presented at the 5th International Electric Propulsion Conference Georgia Institute of Technology Atlanta, Georgia
More informationGRID EROSION MODELING OF THE NEXT ION THRUSTER OPTICS
39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 20-23 July 2003, Huntsville, Alabama AIAA 2003-4868 GRID EROSION MODELING OF THE NEXT ION THRUSTER OPTICS ABSTRACT Results from several different
More informationThrust Balance Characterization of a 200W Quad Confinement Thruster for High Thrust Regimes
Thrust Balance Characterization of a 200W Quad Confinement Thruster for High Thrust Regimes IEPC-2013-155 Presented at the 33rd International Electric Propulsion Conference, The George Washington University
More informationPlasma Thruster Plume Simulation: Effect of the Plasma Quasi Neutrality Hypothesis
CENTROSPAZIO Plasma Thruster Plume Simulation: Effect of the Plasma Quasi Neutrality Hypothesis A. Passaro*, L.Biagioni*, and A.Vicini** * Centrospazio-CPR 56121 Pisa, Italy ** Alta S.p.A. 56121 Pisa,
More informationWall Erosion in 2D Hall Thruster Simulations
Wall Erosion in D Hall Thruster Simulations IEPC-005-189 Presented at the 9 th International Electric Propulsion Conference, Princeton University, Emmanuelle Sommier *, Michelle K. Allis, and Mark A. Cappelli
More informationPRINCETON PLASMA PHYSICS LABORATORY PRINCETON UNIVERSITY, PRINCETON, NEW JERSEY
PREPARED FOR THE U.S. DEPARTMENT OF ENERGY, UNDER CONTRACT DE-AC02-76CH03073 PPPL-3534 UC-70 PPPL-3534 Parametric Investigations of Non-conventional Hall Thruster by Y. Raitses and N.J. Fisch January 2001
More informationCharacterization of an adjustable magnetic field, low-power Hall Effect Thruster
Characterization of an adjustable magnetic field, low-power Hall Effect Thruster IEPC-2011-143 Presented at the 32nd International Electric Propulsion Conference, Wiesbaden Germany S. Oslyak 1, C. Ducci
More informationPlasma Propulsion with electronegative gases
Plasma Propulsion with electronegative gases IEPC-2009-001 Presented at the 31st International Electric Propulsion Conference, University of Michigan Ann Arbor, Michigan USA Ane Aanesland *, Lara Popelier,
More informationParticle Simulation of High Specific Impulse Operation of Low-Erosion Magnetic Layer Type Hall thrusters
Particle Simulation of High Specific Impulse Operation of Low-Erosion Magnetic Layer Type Hall thrusters IEPC-05-5 Presented at Joint Conference of 30th International Symposium on Space Technology and
More informationDevelopment and Research of the Plasma Thruster with a hollow magnet Anode PlaS-40
Development and Research of the Plasma Thruster with a hollow magnet Anode PlaS-40 IEPC-2013-52 Presented at the 33rd International Electric Propulsion Conference, The George Washington University Washington,
More informationEffect of a Plume Reduction in Segmented Electrode Hall Thruster. Y. Raitses, L.A. Dorf, A A. Litvak and N.J. Fisch
Effect of a Plume Reduction in Segmented Electrode Hall Thruster Y. Raitses, L.A. Dorf, A A. Litvak and N.J. Fisch Princeton Plasma Physics Laboratory, P.O. Box 451, Princeton University, Princeton NJ
More information3D simulation of the rotating spoke in a Hall thruster
3D simulation of the rotating spoke in a Hall thruster IEPC-2013-307 Presented at the 33rd International Electric Propulsion Conference, The George Washington University Washington, D.C. USA K. Matyash
More informationDevelopment of Microwave Engine
Development of Microwave Engine IEPC-01-224 Shin SATORI*, Hiroyuki OKAMOTO**, Ted Mitsuteru SUGIKI**, Yoshinori AOKI #, Atsushi NAGATA #, Yasumasa ITO** and Takayoshi KIZAKI # * Hokkaido Institute of Technology
More informationPROTEAN : Neutral Entrainment Thruster Demonstration
PROTEAN : Neutral Entrainment Thruster Demonstration Dr. David Kirtley Dr. George Votroubek Dr. Anthony Pancotti Mr. Michael Pfaff Mr. George Andexler MSNW LLC - Principle Investigator -Dynamic Accelerator
More informationElementary Scaling Relations for Hall Effect Thrusters
JOURNA OF PROPUSION AND POWER Vol. 27, No. 1, January February 2011 Elementary Scaling Relations for Hall Effect Thrusters Käthe Dannenmayer and Stéphane Mazouffre Centre National de la Recherche Scientifique,
More informationLimits on the Efficiency of a Helicon Plasma Thruster
Limits on the Efficiency of a Helicon Plasma Thruster IEPC-05-84 Presented at Joint Conference of 0th International Symposium on Space Technology and Science 4th International Electric Propulsion Conference
More informationAnalyses of the anode region of a Hall thruster channel
38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 7-10 July 2002, Indianapolis, Indiana AIAA 2002-4107 AIAA-2002-4107 Analyses of the anode region of a Hall thruster channel Michael Keidar,
More informationMeasurements of Plasma Potential Distribution in Segmented Electrode Hall Thruster
Measurements of Plasma Potential Distribution in Segmented Electrode Hall Thruster Y. Raitses, D. Staack and N. J. Fisch Princeton University Plasma Physics Laboratory P. O. Box 451, Princeton, NJ 08543
More informationAn introduction to the plasma state in nature and in space
An introduction to the plasma state in nature and in space Dr. L. Conde Departamento de Física Aplicada E.T.S. Ingenieros Aeronáuticos Universidad Politécnica de Madrid The plasma state of condensed matter
More informationHelicon Double Layer Thruster Performance Enhancement via Manipulation of Magnetic Topology
Helicon Double Layer Thruster Performance Enhancement via Manipulation of Magnetic Topology IEPC--97 Presented at the nd International Electric Propulsion Conference, Wiesbaden, Germany S. J. Pottinger,
More informationEffect of a Magnetic Field in Simulating the Plume-Field of an Anode Layer Hall Thruster
Effect of a Magnetic Field in Simulating the Plume-Field of an Anode Layer Hall Thruster Yongjun Choi 1 Uinversity of Michigan, Ann Arbor, MI 48109 Michael Keidar 2 The George Washington University, Washington
More informationINVESTIGATION OF THE POSSIBILITY TO REDUCE SPT PLUME DIVERGENCE BY OPTIMIZATION OF THE MAGNETIC FIELD TOPOLOGY IN THE ACCELERATING CHANNEL
IEPC-97-154 945 INVESTIGATION OF THE POSSIBILITY TO REDUCE SPT PLUME DIVERGENCE BY OPTIMIZATION OF THE MAGNETIC FIELD TOPOLOGY IN THE ACCELERATING CHANNEL Michael Day, international Space Technology, Inc.,
More informationStudy on Anomalous Electron Diffusion in the Hall Effect Thruster
Paper DOI:10.5139/IJASS.2014.15.3.23 Study on Anomalous Electron Diffusion in the Hall Effect Thruster Kybeom Kwon* Department of Aerospace Engineering, Air Force Academy, Chungbuk, 363-849, Republic of
More informationWhat We Have Learned By Studying The P5 Hall Thruster
What We Have Learned By Studying The P5 Hall Thruster Alec D. Gallimore Director of the Plasmadynamics and Electric Propulsion Laboratory Department of Aerospace Engineering The University of Michigan
More informationThe Experimental Study on Electron Beam Extraction from ECR Neutralizer
The Experimental Study on Electron Beam Extraction from ECR Neutralizer IEPC-2015-b-105 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International
More informationPhysics of Hall-Effect Discharge by Particle
Physics of Hall-Effect Discharge by Particle IEPC-2013-148 Presented at the 33rd International Electric Propulsion Conference, The George Washington University Washington, D.C. USA F. Taccogna 1 P. Minelli
More informationParticle Simulation of Plasma Energy Deposition on Hollow Cathode Insert
Particle Simulation of Plasma Energy Deposition on Hollow Cathode Insert IEPC-17-33 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology Atlanta, Georgia USA
More information2D simulations of Hall thrusters
Center for Turbulence Research Annual Research Briefs 1998 81 2D simulations of Hall thrusters By Eduardo Fernandez, Mark Cappelli, AND Krishnan Mahesh 1. Motivation and objectives Closed-Drift (Hall)
More information27 th IEEE International Conference on Plasma Science New Orleans, LA June 4-7, Optimization of Hall Thruster Magnetic Field Topography
27 th IEEE International Conference on Plasma Science New Orleans, LA June 4-7, Optimization of Hall Thruster Magnetic Field Topography Richard R. Hofer, James M. Haas, Peter Y. Peterson, Rafael A. Martinez
More informationspacecraft mass = kg xenon ions speed = m s 1 Fig. 2.1 Calculate the mass of one xenon ion. molar mass of xenon = 0.
1 (a) A solar-powered ion propulsion engine creates and accelerates xenon ions. The ions are ejected at a constant rate from the rear of a spacecraft, as shown in Fig. 2.1. The ions have a fixed mean speed
More informationMethods of Controlling Low-Frequency Oscillation in a Hall Thruster *
Methods of Controlling Low-Frequency Oscillation in a Hall Thruster * Takeshi Furukawa, Takeshi Miyasaka and Toshi Fujiwara Department of Aerospace Engineering, Nagoya University Furo, Chikusa-ku Nagoya
More informationCommissioning of the Aerospazio s vacuum facilities with Safran s Hall Effect Thruster
Commissioning of the Aerospazio s vacuum facilities with Safran s Hall Effect Thruster IEPC-2017-414 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology Atlanta,
More informationInvestigation of SPT Performance and Particularities of it s Operation with Kr and Kr/Xe Mixtures *+
Investigation of SPT Performance and Particularities of it s Operation with Kr and Kr/Xe Mixtures *+ Vladimir Kim, Garry Popov, Vyacheslav Kozlov, Alexander Skrylnikov, Dmitry Grdlichko Research Institute
More informationSPT Operation in Machine-Gun Mode
SPT Operation in Machine-Gun Mode IEPC-005-6 Presented at the 9 th International Electric Propulsion Conference, Princeton University, October 3 November 4, 005 AIBugrova *, ASLipatov and SVBaranov Moscow
More informationINTEGRAL AND SPECTRAL CHARACTERISTICS OF ATON STATIONARY PLASMA THRUSTER OPERATING ON KRYPTON AND XENON
1 INTEGRAL AND SPECTRAL CHARACTERISTICS OF ATON STATIONARY PLASMA THRUSTER OPERATING ON KRYPTON AND XENON A.I.Bugrova, A.I.Morozov *, A.S.Lipatov, A.M.Bishaev, V.K.Kharchevnikov, M.V.Kozintseva. Moscow
More informationOPERATIONAL CHARACTERISTICS OF CYLINDRICAL HALL THRUSTERS
OPERATIONAL CHARACTERISTICS OF CYLINDRICAL HALL THRUSTERS Atsushi Shirasaki, Hirokazu Tahara and Takao Yoshikawa Graduate School of Engineering Science, Osaka University -, Machikaneyama, Toyonaka, Osaka
More informationDesign and Construction of an Electron Trap for Studying Cross- Field Mobility in Hall Thrusters
43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 8-11 July 2007, Cincinnati, OH AIAA 2007-5207 Design and Construction of an Electron Trap for Studying Cross- Field Mobility in Hall Thrusters
More information