Kinetic PIC Modeling of Ion Beam Neutralization

Kinetic PIC Modeling of Ion Beam Neutralization

Ion beam neutralization is a significant challenge in electric propulsion and is needed to reduce beam electric fields, manage space charge, and reduce ion sputter of the spacecraft. To address these challenges, simulation can be used to investigate ion/electron interactions, predict space charge distributions, and optimize system properties, such as cathode location, beamlet current, ion density, and electron temperature. However, beam neutralization can be a challenging problem to simulate due to the extreme difference in mass between ions and electrons as well as the complex interaction of electromagnetic forces.

VizGrain is used to model the beam neutralization using a full, kinetic particle-in-cell (PIC) modeling approach. Both ions and electrons are modeled as kinetic particles. Typical simulation approaches in literature involve initializing both ion and electron beams from a single, pre-mixed source. This example simulates a configuration in which the electron beam source is located outside of the ion beam. This allows us to investigate the initial mixing and entrainment of the electrons.

The 2D simulation geometry is shown in the Figure 1.

Figure 1: Beam neutralization geometry and simulation setup

The spacecraft, shown in green, is set to a reference of 0 V. The electron beam, shown in blue, is injected with a temperature of 2 eV. The ion beam, shown in red, has a beamlet current of 5mA. To adequately resolve the electrostatic potential required to model ion and electron interaction, the Debye length must be resolved in the mesh.  The resulting mesh is ~400K cells using a structured/unstructured mixed meshing approach.

Animations of the results are shown in Figures 2 and 3. Figure 2 shows the electrostatic potential with the interaction of ions (red) and electrons (blue). Figure 3 colors the particles by velocity.

Figure 2: Beam neutralization animation of electrostatic potential, ions = red, electrons = blue

Figure 3: Beam neutralization animation with particles colored by velocity

The electrostatic potential of the ion beam attracts and entrains the electrons. As shown in the velocity plot, the electrons are accelerated as they enter the electrostatic potential well created by the ion beam, then slow down as they exit the beam. Additionally, an instability can be observed in the electron beam in which the electrons begin to oscillate around the ion beam. The magnitude of the oscillations will likely decrease as the neutralization approaches steady state.

Finally, Figure 4 compares the electrostatic potential with and without electron neutralization.

Figure 4:  Electrostatic potential with and without electron neutralization

As expected the electron beam greatly reduces the potential, effectively neutralizing the beam. Note that the minimal ion beam divergence for the case without neutralization is attributed to the low beamlet current.

This example demonstrates VizGrain’s PIC modeling capability for electric propulsion applications. VizGrain is the 1D/2D/3D kinetic particle module within the OverViz Simulation Suite that provides scalable parallel simulation for large, complex problems. OverViz is an industrial multiphysics framework for performing hybrid plasma, fluid flow, electromagnetic, particle simulations. For more information, please contact us at info@esgeetech.com.

 

Esgee to Present at SCTC 2018: Modeling of Spacecraft Charging in GEO orbit

Esgee to Present at SCTC 2018: Modeling of Spacecraft Charging in GEO orbit

Esgee will present “High-fidelity Multi-Length Scale Modeling of Spacecraft Charging in GEO orbit” at the 15th Spacecraft Charging Technology Symposium 25-29 June, 2018 at the Integrated Research Center of Kobe University in Japan.

 

Abstract

This study describes high-fidelity modeling of spacecraft charging in GEO orbit environment and the resulting incipient vacuum arcing on the spacecraft’s surface. A satellite in GEO environment is subject to continuous bombardment by highly energetic charged particles that accumulate over time on dielectric surfaces resulting in differential voltages between surfaces.  For sufficiently large differential voltages, the electric field at sharp corners or protrusions may exceed the threshold for field electron emission that is accompanied by explosive emission of material from the feature.  This event constitutes the start of a vacuum arcing event with resulting damage to the spacecraft structure.  In this work, a high-fidelity computational model with unstructured meshing framework is used.  This framework allows of a multi-length scale resolution of small spacecraft features while fully representing the entire spacecraft geometry.  The self-consistent electrostatic potential equation is solved in conjunction with particle tracking to resolve electric-field profiles on the spacecraft surface. Further, the effects of a variety of surface electron emission processes (including secondary electron and photoelectron emission) is represented.

 

Esgee to Present at SCTC 2018: Hybrid Model of RF Gridded Ion Thruster

Esgee to Present at SCTC 2018: Hybrid Model of RF Gridded Ion Thruster

Esgee will present “Hybrid Fluid-Particle Plasma Modeling of a Radio-Frequency Gridded Ion” at the 15th Spacecraft Charging Technology Symposium 25-29 June, 2018 at the Integrated Research Center of Kobe University in Japan.

 

Abstract

We present a hybrid, fluid-particle plasma model that is used to investigate the plasma discharge and ion extraction behaviors of a radio-frequency gridded ion thruster (RIT). The hybrid approach combines a fluid formulation for plasma governing equations with a kinetic particle formulation for ion behaviors. The self-consistent plasma model includes fully coupled electromagnetics and RF circuit models. Ion particles are dynamically generated from ionization rates in the discharge and tracked as they are extracted from the chamber by a series of electrostatically biased grids. This hybrid approach offers an accurate representation of ion optics coupled with an efficient representation of bulk plasma discharge and chamber operating conditions within a single coupled simulation.

Results are presented for an axisymmetric model of an RIT-3.5. Predicted ion density distributions and ion optics are compared to literature with reasonable agreement. Performance sensitivity to grid potentials are studied to demonstrate model application to thruster performance optimization. The OverViz Simulation Suite, with coupled non-equilibrium plasma and kinetic particle modules, is used to perform the simulations.