Computational model of a Hall thruster

Koo, Justin; Boyd, Iain D.

doi:10.1016/j.cpc.2004.06.058

Cited by 29 publications

(25 citation statements)

References 5 publications

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“…is the potential difference between the anode and the presheath edge, k is [4]. Thus, Koo did not suggest a preference for one mechanism over the other.…”

Section: Physics Modelmentioning

confidence: 97%

Study on Anomalous Electron Diffusion in the Hall Effect Thruster

Kwon¹,

Walker²,

Mavris³

2014

International Journal of Aeronautical and Space Sciences

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Over the last two decades, numerous experimental and numerical efforts have examined physical phenomena in plasma discharge devices. The physical mechanisms that govern the anomalous electron diffusion from the cathode to the anode in the Hall Effect Thruster (HET) are not fully understood. This work used 1-D numerical method to improve our understanding and gain insight into the effect of the anomalous electron diffusion in the HET. To this end, numerical solutions are compared with various experimental HET performance measurements and the effects of anomalous electron diffusion are analyzed. The relationships between the anomalous electron diffusion and important parameters of the HET are also studied quantitatively. The work identifies the cathode mass flow rate fraction, radial magnetic field distribution, and discharge voltage as significant factors that affect anomalous electron diffusion. Additionally, the study demonstrates a computational process to determine the radial magnetic field distribution required to achieve specific thruster performance goals.

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“…is the potential difference between the anode and the presheath edge, k is [4]. Thus, Koo did not suggest a preference for one mechanism over the other.…”

Section: Physics Modelmentioning

confidence: 97%

Study on Anomalous Electron Diffusion in the Hall Effect Thruster

Kwon¹,

Walker²,

Mavris³

2014

International Journal of Aeronautical and Space Sciences

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“…Particle colliding with boundary and with each other are considered in this model [21]. The effective electron collision frequency related to the anomalous transport (Bohm diffusion) ν B = αω ce is also considered in the model, where α = 1/64 is the empirical parameter in Hall thrusters which has been validated by many fluid and hybrid results as shown in [22,23]. Furthermore, the SEE caused by electron-wall collision is considered on both the dielectric (BN) wall surface and the low-emissive electrodes (graphite) wall surface; for this purpose, an improved SEE model [24] based on that of Morozov is applied.…”

Section: Numerical Modelmentioning

confidence: 99%

Particle‐in‐Cell Simulation for the Effect of Segmented Electrodes Near the Exit of an Aton‐Type Hall Thruster on Ion Focusing Acceleration

Qing

Liu

et al. 2011

Contrib. Plasma Phys.

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The effect of floating conductive electrodes near the channel exit of an Aton-type Hall thruster on ion focusing acceleration is studied by simulating the two-dimensional plasma flow with a fully kinetic Particle-in-Cell method for the gas flow rate ja ranged in 1∼3 mg/s. Numerical results show that low-emissive electrodes can reduce plume divergence if the electrode length is less than 2 mm due to the low secondary electron emissive characteristic, but widen plume in all the gas flow rate range if the electrode length is greater than 2mm since the conductive property of segmented electrodes trends to make equipotential lines convex toward channel exit and is even parallel to the wall surface in the near-wall region. Further investigation predicts that the combination of high emissive dielectric wall and segmented low-emissive dielectric wall is a promising way to reduce plume divergence.

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“…Same set of cases presented in the previous paragraph was run with the wall potential modified by the presence of SEE. We include secondary electrons in our code by computing the SEE emission coefficient using Equation 4. From the wall potential relationship, Equation 5, we can see that the presence of SEE acts to decrease the sheath potential and hence the sheath thickness.…”

Section: Influence Of Secondary Electron Emissionmentioning

confidence: 99%

“…2,3 Other researchers have developed their own codes based on the basic premise of HPHall. [4][5][6][7] These codes share a common approach. Ions are treated as kinetic particles while electrons are modeled as a quasi-1D fluid.…”

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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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Computational model of a Hall thruster

Cited by 29 publications

References 5 publications

Study on Anomalous Electron Diffusion in the Hall Effect Thruster

Study on Anomalous Electron Diffusion in the Hall Effect Thruster

Particle‐in‐Cell Simulation for the Effect of Segmented Electrodes Near the Exit of an Aton‐Type Hall Thruster on Ion Focusing Acceleration

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

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