Particle Simulations of a Hall Thruster Plume

This paper describes two modeling approaches developed at Lockheed Martin Missiles and Space Operations for analysis of the sputter erosion of spacecraft surfaces due to use of Hall thrusters. The PIC-DSMC (Particle in Cell-Direct Simulation Monte Carlo) plume model developed at Massachusetts Institute of Technology was successfully modified to model the BPT-4000 thruster (4.5 kW, 350 V) plumes. In addition to modeling the complicated plume features using the PIC-DSMC code, we also developed a semi-empirical plume model that requires less computational time for modeling the sputter erosion of spacecraft surfaces. The approach uses PLIMP (Plume Impingement) code as a ray-tracing tool to determine the plume distances from the exit to impinged objects (e.g. solar arrays), plume divergence angles, and impingement angles. Measured ion current flux and sputter rates were then used to examine the sputtering erosion for solar arrays on a representative geostationary spacecraft. This simi-empirical model allows one to perform a quick spacecraft-plume interaction investigation. Moreover, contamination deposition of eroded thruster products and sputtered spacecraft materials was examined.

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“…Boyd and Martinez-Sanchez and their students (Refs. [11][12][13]. Details of the improvements made in the subsequent work are summarized in Refs.…”

Section: Particle Approachmentioning

confidence: 99%

<title>Modeling of Hall thruster plume sputtering and contamination</title>

Chang

Wittenauer

Lichtin

et al. 2000

Optical Systems Contamination and Degradation II: Effects, Measurements, and Control

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“…The Express data is the first set of measurements obtained in-orbit for the plume of a Hall thruster. Figure 6 shows an example from the work of Van Gilder et al 8 that illustrates the levels of agreement that have been achieved between these plume models and the laboratory data, for ion current density. One of the main questions to be answered in this study is whether these same models are able to predict the space-flight data.…”

Section: Ion Current Densitymentioning

confidence: 99%

Hall thruster far field plume modeling and comparison to Express flight data

Boyd¹

2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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Hall thrusters are an attractive form of electric propulsion that are being developed and implemented to replace chemical systems for many on orbit propulsion tasks on communications satellites. One concern in the use of these devices is the possible damage their plumes may cause to the host spacecraft. Computer models of Hall thruster plumes play an important role in integration of these devices onto spacecraft as the space environment is not easily reproduced in ground testing facilities. In this paper, a hybrid particle-fluid model of a Hall thruster plume is applied to model the SPT-100 thrusters used on the Russian Express satellites. The emphasis of the paper is on making assessment of the model through direct comparison with measurements of ion current density and ion energy distributions taken on board Express spacecraft.These data challenge the model in two ways. First, they represent the first set of Hall thruster plume measurements obtained in space, whereas the computer models have been developed based on measurements taken in ground-based facilities. Second, most of the data measurement locations are several meters from the thruster requiring careful consideration of the plume far-field.

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“…Distribution A: Distribution Unlimited 2 Despite much research and development in modeling plume expansion, 3,4,5,6 it is necessary to continuously validate these codes using laboratory based experimental data. This paper presents a study that compares results from an AQUILA simulation to experimental data from the BHT-HD-600 Hall thruster.…”

Section: American Institute Of Aeronautics and Astronauticsmentioning

confidence: 99%

Comparison of Hall Thruster Plume Expansion Model with Experimental Data

Niemela¹,

Cheng²,

Brieda³

et al. 2006

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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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 SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force ABSTRACTNumerical modeling of the expansion of electric thruster plumes provides direct means for predicting spacecraft surface contamination and erosion due to plume ions. A software package named COLISEUM that is capable of self-consistently modeling plasma propagation and interactions with arbitrary 3-D surfaces is being developed by a national team of researchers. Despite much research and development in modeling plume expansion, it is necessary to continuously validate these codes using laboratory based experimental data. It is well-established that vacuum chamber facilities affect the plume of these devices. Thus, the models must not only describe the plume expansion, but also effects of the vacuum chamber. COLISEUM has been designed to simulate both vacuum chamber configurations and spacecraft geometries. This work provides source derivation from laser induced florescence (LIF) data. Included is a study that compares results from a hybrid particle-in-cell model (AQUILA) with Monte Carlo collisions to data obtained from the plume of Busek 600W Hall thruster (BHT-HD-600). This data includes current density, velocity distribution, and energy data. Numerical modeling of the expansion of electric thruster plumes provides direct means for predicting spacecraft surface contamination and erosion due to plume ions. A software package named COLISEUM that is capable of self-consistently modeling plasma propagation and interactions with arbitrary 3-D surfaces is being developed by a national team of researchers. Despite much research and development in modeling plume expansion, it is necessary to continuously validate these codes using laboratory based experimental data. It is well-established that vacuum chamber facilities affect the plume of these devices. Thus, the models must not only describe the plume expansion, but also effects of the vacuum chamber. COLISEUM has been designed to simulate both vacuum chamber configurations and spacecraft geometries. This work presents a study that compares results from a hybrid particle-in-cell model (AQUILA) with Monte Carlo collisions to data obtained from the plume of Busek 600W Hall thruster (BHT-HD-600). This data includes current density, ion velocities, and energy distribution data. Also contained in this work is a source derivation description from laser induced fluorescence (LIF) data.

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Particle Simulations of a Hall Thruster Plume

Cited by 39 publications

References 16 publications

<title>Modeling of Hall thruster plume sputtering and contamination</title>

<title>Modeling of Hall thruster plume sputtering and contamination</title>

Hall thruster far field plume modeling and comparison to Express flight data

Comparison of Hall Thruster Plume Expansion Model with Experimental Data

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