Further Development and Preliminary Results of the AQUILA Hall Thruster Plume Model

Santi, Mark; Cheng, Shannon Y.; Çelik, Murat; Martı́nez-Sánchez, Manuel; Peraire, J.; Solver, Non-Neutral

doi:10.2514/6.2003-4873

Cited by 13 publications

(7 citation statements)

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“…These data have been used extensively for model validation. [22][23][24][25][26][27][28][29] The experimental data from this effort are compared to simulations of the plume performed using plasma plume model DRACO. DRACO is an electrostatic particle-in-cell (PIC) code used to simulate plume of electric propulsion devices.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Examination of a Hall Thruster Plume (Preprint)

Nakles¹,

Brieda²,

Reed³

et al. 2007

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Research Laboratory (AFMC) AFRL/PRS SPONSOR/MONITOR'S Pollux Drive NUMBER(S)Edwards AFB CA 93524-7048 AFRL-PR-ED-TP-2007-380 DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution unlimited (PA #07313A). 14. ABSTRACT The plume of a Busek BHT-200 xenon Hall thruster has been characterized through measurements from various plasma electrostatic probes. Ion current flux, plasma potential, plasma density, and electron temperatures were measured from the near-field plume to 60 cm downstream of the exit plane. These experimentally derived measurements were compared to numerical simulations run with the plasma plume code DRACO. A major goal of this study was to determine the fidelity of the DRACO numerical simulation. The effect of background pressure on the thruster plume was also examined using ion current flux measurements at higher than nominal pressure. The plume of a Busek BHT-200 xenon Hall thruster has been characterized through measurements from various plasma electrostatic probes. Ion current flux, plasma potential, plasma density, and electron temperatures were measured from the near-field plume to 60 cm downstream of the exit plane. These experimentally derived measurements were compared to numerical simulations run with the plasma plume code DRACO. A major goal of this study was to determine the fidelity of the DRACO numerical simulation. The effect of background pressure on the thruster plume was also examined using ion current flux measurements at higher than nominal pressure.

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Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Examination of a Hall Thruster Plume (Preprint)

Nakles¹,

Brieda²,

Reed³

et al. 2007

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“…While the collision model has been reported to have been successful in previous studies, 2,3,8,14 a systematic validation of the collision model source code has not been found by the authors. Another suggested improvement to address the remaining differences between the subcycling and the fine time step cases is to perform the collision modeling between the high speed particles and the rest of the particles within the subcycle loop.…”

mentioning

confidence: 88%

“…A hybrid Particle-in-Cell plasma model within COLISEUM, called AQUILA, 2 is the basis of this work. The COLISEUM framework is used to model the thrusters in space environment for prediction of the interactions and also to model the thrusters in vacuum chambers in order to validate the models used in COLISEUM against experimental data.…”

Section: Nomenclaturementioning

confidence: 99%

Investigation of Particle-in-Cell Acceleration Techniques for Plasma Simulations

Marshall

VanGilder

2006

37th AIAA Plasmadynamics and Lasers Conference

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information ABSTRACTCOLISEUM is an application framework that integrates plasma propagation schemes and arbitrary 3D surface geometries. Using Particle-in-Cell (PIC) schemes to model the plasma propagation high fidelity modeling of the plasma and its interaction with the surfaces is possible. In order to improve the computational performance of the Particle-in-Cell (PIC) scheme within COLISEUM (AQUILA), accelerate techniques have been developed that significantly decrease the amount of CPU time needed to obtain a stead-state solution. These schemes have been demonstrated to decrease the CPU time from 3 to 24 times with little appreciable differences in the global particle properties and number densities. This work investigates the differences in the local plasma properties that result from the application of the different acceleration techniques. In particular, the number densities and velocity distributions of the ions and neutrals demonstrate that the solution acceleration schemes produce very similar solutions outside the main path of the plasma source. Within the main path of the plasma source the local plasma properties show marked differences that might be associated with the time steps associated with these schemes and/or the collision modeling scheme within AQUILA. SECURITY CLASSIFICATION OF:17 COLISEUM is a application framework that integrates plasma propagation schemes and arbitrary 3D surface geometries. Using Particle-in-Cell (PIC) schemes to model the plasma propagation high fidelity modeling of the plasma and its interaction with the surfaces is possible. In order to improve the computational performance of the Particle-in-Cell (PIC) scheme within COLISEUM (AQUILA), accelerate techniques have been developed that significantly decrease the amount of CPU time needed to obtain a steady-state solution. These schemes have been demonstrated to decrease the CPU time from 3 to 24 times with little appreciable differences in the global particle properties and number densities. This works investigates the differences in the local plasma properties that result from the application of the different acceleration techniques. In particular, the number densities and velocity distributions of the ions and neutrals demonstrate that the solution acceleration schemes produce very similar solutions outside of the main path of the plasma source. Within the main path of the plasma source the local plasma properties show marked differences that might be associated with the time steps associated with these schemes and...

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“…26 Prior to commencing the solver iterations, the solver calculates the local Debye length at each node of the simulation domain. If , where V is the cell volume, the node is flagged as quasineutral and potential on it is fixed to the value obtained by the direct inversion.…”

Section: B Hybrid Potential Solvermentioning

confidence: 99%

Multi-Scale Modeling of Novel Hall Thrusters: Understanding Physics of CHT and DCF Thrusters

Keidar¹

2011

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. (30-12-2011) (From -To) 01 May 10-30 Apr. 11 REPORT DATE REPORT TYPE Final DATES COVERED TITLE AND SUBTITLE 5a. CONTRACT NUMBERMulti-scale modeling of novel Hall thrusters: understanding physics of CHT and DCF Thrusters PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) AND ADDRESS(ES) PERFORMING ORGANIZATION REPORT NUMBERGeorge Washington University SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)AFOSR, Dr. Mitat Birkan SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION / AVAILABILITY STATEMENT SUPPLEMENTARY NOTES ABSTRACTIn order to simulate the magnetized plasma thruster devices (such as CHT, DCF etc) we have developed a multi-scale numerical code that is based on coupling of a PIC/MCC analysis of neutrals and ions in a general 2D domain (or 3D) and a 1D kinetic full PIC treatment of electrons along magnetic fields. The implementation of such a two-way coupling allows calculation of the electron transport in the real physical domain while significantly reducing the computational time associated with 2D full kinetic simulations. The objective of this study was to identify the individual contribution to transport from factors such as collisions, surface roughness, secondary electron emission, and plasma oscillations. Multi-scale model of the magnetized plasma thruster discharge in which a kinetic treatment was used for the electron component while a 2D (or 3D) macroscopic model will be employed for ion and neutral component analysis. Initial coupling of the microscopic and macroscopic model was performed via axial electric field, electron fluxes to the wall and electron cross-field transport. This model demonstrated improved prediction of electron mobility. AbstractIn order to simulate the magnetized plasma thruster devices (such as CHT, DCF etc) we have developed a multi-scale numerical code that is based on coupling of a PIC/MCC analysis of neutrals and ions in a general 2D domain (or 3D) and a 1D kinetic full PIC treatment of electrons along magnetic fields. The implementation of such a two-way coupling allows calculation of the electron transport in the real physical d...

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Further Development and Preliminary Results of the AQUILA Hall Thruster Plume Model

Cited by 13 publications

References 1 publication

Experimental and Numerical Examination of a Hall Thruster Plume (Preprint)

Experimental and Numerical Examination of a Hall Thruster Plume (Preprint)

Investigation of Particle-in-Cell Acceleration Techniques for Plasma Simulations

Multi-Scale Modeling of Novel Hall Thrusters: Understanding Physics of CHT and DCF Thrusters

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