Towards Self-Consistent Simulation of Radial Effects on an Axial PIC Model of the Hall Discharge - IEPC-2024-699

Sep 4, 2026

Wall interactions play a decisive role in Hall thruster plasma behavior, yet full 3D kinetic Particle-In-Cell modeling is computationally prohibitive. This work presents a new wall interaction model for an axial PIC formulation, introducing a radial potential profile that distinguishes presheath from an infinitely thin sheath. Electrons and ions move radially according to this prescription, while particle removal is based on their radial energy relative to the sheath potential, capturing kinetic plasma-wall effects. Accuracy is validated against comparable axial-radial PIC results and robustness is assessed with respect to numerical parameters.

LanguageEnglish

CategoryResearch & Report

FormatPDF

Pages15

Reading Time38 min

AccessFree to download

Introduction

Background on reduced-dimensionality Hall thruster modeling

Need to include radial wall effects in PIC simulations

Prior wall-interaction approaches and limitations

Proposed wall interaction model and validation plan

Towards self-consistent simulation of radial effects on an axial PIC model of the Hall discharge IEPC-2024-699 Presented at the 38th International Electric Propulsion Conference, Toulouse, France June 23-28, 2024 Guillermo Cuerva-L´azaro∗, Enrique Bello-Ben´ıtez†, Alberto Mar´ın-Cebri´an‡, and Eduardo Ahedo§ Department of Aerospace Engineering, Universidad Carlos III de Madrid, Legan´es, Madrid, 28911, Spain The computational demands of 3D kinetic modeling of a Hall Thruster discharge are significant, requiring substantial resources and often resulting in impractically long computation times. As a result, reduced-dimensionality codes are commonly employed, some incorporating the effects of the unmodeled dimension(s) . In this work, we introduced anew model to study wall interactions in a PIC simulation. Our model moves electrons and ions radially by prescribing a radial potential profile that differentiates between presheath and infinitely thin sheath. Particle removal is determined based on their radial energy relative to the sheath potential, allowing for kinetic effects on plasma-wall interactions. As a proof of concept, we include this model in axial PIC simulations of a Hall thruster discharge, assessing its physical accuracy, comparing the results with similar axial-radial PIC simulations, and evaluating its robustness against numerical parameters. This new wall interaction model could, in the future, be coupled with axial-azimuthal PIC simulations serving as an effective middle ground between computationally expensive 3D kinetic modeling and traditional 2D axial-azimuthal PIC simulations. ∗ PhD student, Department of Aerospace Engineering, [gcuerva@ing.uc3m.es](gcuerva@ing.uc3m.es)[ ](gcuerva@ing.uc3m.es)†PhD student, Department of Aerospace Engineering, [ebello@ing.uc3m.es](ebello@ing.uc3m.es)[ ](ebello@ing.uc3m.es)‡PhD student, Department of Aerospace Engineering, [almarinc@pa.uc3m.es](almarinc@pa.uc3m.es) § Professor, Department of Aerospace Engineering, eahedo@ing.uc3m.es 1 The 38th International Electric Propulsion Conference, P. Baudis Convention Center, Toulouse, France, June 23-28, 2024 Copyright 2024 by the Electric Rocket Propulsion Society. All rights reserved. Nomenclature e = Fundamental charge nn = Neutral density uzn = Neutral average axial velocity m˙ = Neutral mass flow Tn = Neutral temperature m˙zi = Axial ion flow mi = Ion mass ni = Ion density Ti = Ion temperature cs = Ion sound velocity uzn = Ion axial velocity uriQ = Ion radial velocity at sheath edge Sprod = Source term due to ionization me = Electron mass ne = Electron density Te = Electron temperature pe = Electron pressure Er = Radial Electric field Bm = Maximum magnetic field ϕsh = Potential drop at the sheath ϕ∗sh = Theoretical potential drop at the sheath δϕsh = Perturbation of potential drop at the sheath j∗W = Theoretical wall current jW = Wall current density IW = Wall current ϕ = Electric potential νe = Effective electron collision frequency αano = Anomalous coefficient I∞ = Plume current Vd = Discharge voltage Id = Discharge current rW = Wall radius Lr = Channel width Lch = Channel length A = Channel cross-section zm = Location of maximum magnetic field lm = Exponential decay length of the magnetic field c˜ = artificial capacitance wp = Particle weight ∆l = Grid size ∆t = Time-step fD = Augmentation factor ϵ0 = Vacuum permittivity ωce = Electron cyclotron frequency νe = Electron effective collision frequency HET = Hall Effect Thruster PIC = Particle-In-Cell MCC = Monte Carlo Collision 2 The 38th International Electric Propulsion Conference, P. Baudis Convention Center, Toulouse, France, June 23-28, 2024 Copyright 2024 by the Electric Rocket Propulsion Society. All rights reserved. I. Introduction The 3D kinetic modeling of a Hall Thruster discharge requires extensive resources and sometimes unfeasible computation

FAQs

Why are reduced-dimensional PIC models commonly used for Hall thruster discharges?

3D kinetic modeling demands extensive computational resources and can lead to impractically long computation times. Reduced 1D/2D approaches are therefore used to simulate the discharge more efficiently.

How does the proposed wall interaction model treat electron and ion motion?

The model moves electrons and ions radially by prescribing a radial potential profile that differentiates between the presheath and an infinitely thin sheath.

How does the model decide when particles are removed at the wall?

Particle removal is determined by comparing each particle’s radial energy with the sheath potential, enabling kinetic effects on plasma-wall interactions.

Sep 4, 2026

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