Kinetic Analysis of Electron Transport in a Cylindrical Hall Thruster

Brieda, Lubos; Pai, S. T.; Keidar, Michael

doi:10.1109/tps.2011.2159741

Cited by 4 publications

(3 citation statements)

References 4 publications

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“…In our previous work 14 we performed a limited parametric study where we investigate several different cathode line positions and Bohm parameters with the goal of matching the experimental measurements for CHT. We were able to improve our correlation for this work.…”

Section: Initial Results For Thruster Dischargementioning

confidence: 99%

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

Keidar¹

2011

Self Cite

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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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Section: Initial Results For Thruster Dischargementioning

confidence: 99%

“…This finding was touched upon in our previous work. 14 The walls of this SPT-type thruster are made of a dielectric material. The dielectric walls distinguish this thruster design from another Hall thruster variant, TAL (thruster with anode layer), in which the walls are conductive.…”

Section: Thruster Detailsmentioning

confidence: 99%

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

Keidar¹

2011

Self Cite

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“…In addition to the exchange of kinetic energy, the internal state of the particles changed during the collision or transformed into other particles is called inelastic scattering. Inelastic scattering can be divided into single-electron excitation and plasma excitation [24][25][26][27]. Inelastic scattering is characterized by the energy loss function (ELF), in which the dielectric function reflects the response of the solid to external electromagnetic perturbations.…”

Section: Inelastic Scattering Propertiesmentioning

confidence: 99%

Modelling the Impact of Graphene Coating of Different Thicknesses on Polyimide Substrate on the Secondary Electron Yield

Qi,

Ma,

Liu

et al. 2023

Coatings

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Polyimide material is widely used in the aerospace field, but its secondary electron emission yield is high. In this study, a graphene coating was used to suppress its secondary electron emission, and the secondary electron emission yield of graphene-coated materials with different thicknesses was calculated using the GEANT4 numerical simulation method. The suppression effect of different thicknesses of graphene coatings on the secondary electron emission was analyzed. The simulation results showed that the optimal graphene coating thicknesses for the lowest secondary electron yield of polyimide materials were 1 nm and 5 nm, which reduced the secondary electron emission yield by 13% in terms of simulation. The 5 nm graphene coating reduced the secondary electron emission yield by 6% compared to the polyimide material from an experimental perspective. The 5 nm coating showed better results at higher energies and was experimentally verified by preparing five layers of graphene coating, which showed good agreement between the simulation and experiment. Meanwhile, with the increase in graphene coating thickness, the surface secondary electron emission displacement range decreased, and the secondary electrons produced at the surface were of low energy. The results of this study can provide technical reference for polyimide in aerospace applications and secondary electron emission simulation.

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Plasma in Space Propulsion

Keidar¹,

Beilis²

2013

Plasma Engineering

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Kinetic Analysis of Electron Transport in a Cylindrical Hall Thruster

Cited by 4 publications

References 4 publications

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

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

Modelling the Impact of Graphene Coating of Different Thicknesses on Polyimide Substrate on the Secondary Electron Yield

Plasma in Space Propulsion

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