Validation of Hall thruster plume sputter model

Kannenberg, Keith; Khayms, Vadim; Emgushov, Brian; Werthman, Lance; Pollard, James E.

doi:10.2514/6.2001-3986

Cited by 8 publications

(6 citation statements)

References 1 publication

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“…For each combination of incident and target materials, the sputtered material and the sputtering model with appropriate coefficients can be specified in the input file. Currently, seven different models for total sputter yield are implemented: the constant yield model and models by Matsunami et al, 15 Yamamura and Tawara, 16 Kannenberg et al, 17 Roussel et al, 18 Garnier et al, 19 and Pencil et al 20 Yamamura and Tawara's model is the most general and agrees fairly well with many combination of source and target materials. Examples of sputtering yield curves as functions of energy and angle are shown in Fig.…”

Section: E Particle-surface Interactionmentioning

confidence: 98%

SM/MURF: Current Capabilities and Verification as a Replacement of AFRL Plume Simulation Tool COLISEUM

Araki¹,

Martin²,

Bilyeu³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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Section: E Particle-surface Interactionmentioning

confidence: 98%

SM/MURF: Current Capabilities and Verification as a Replacement of AFRL Plume Simulation Tool COLISEUM

Araki¹,

Martin²,

Bilyeu³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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“…These processes present a complex spacecraft interaction problem of determining where net erosion or net deposition of material will occur. In standard practice the approach to this problem is to use witness plates [1][2][3][4]. Typically witness plates are placed downstream of a thruster at different angular positions in ground-based test facilities to determine the relative importance of the competing effects of (1) sputter rates caused by energetic plume ions and (2) deposition rates caused by sputtered thruster materials.…”

Section: Introductionmentioning

confidence: 99%

“…At Space Systems Loral (SS/L), a detailed SPT-100 HET plume model has been developed that incorporates ion current density, ion energy and sputter yield data. Among several other capabilities this model has the ability to calculate net erosion or net thruster material deposition rates at points of interest on a given satellite [1][2][3][4].…”

Section: Introductionmentioning

confidence: 99%

Influence of residual gases on witness plate measurements during Hall-effect thruster testing

Williams

Corey²

2010

Plasma Sources Sci. Technol.

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It is known that the presence of residual gases can significantly suppress the sputter erosion rate of surfaces. Concerns about the validity of witness plate measurements are raised when this happens in ground-based tests of plasma thrusters. Here we quantify the influence residual gases impose upon measurements made with witness samples placed within the energetic ion plume of a Hall-effect plasma thruster. Specifically, sputter rates of thin films composed of iron by xenon ions are presented as functions of ion energy and partial pressure of molecular oxygen and nitrogen. When gas contaminates are present, the sputter rate is determined as a function of the poisoning ratio, R p , defined as the rate of arrival of contamination sticking to a surface divided by the removal rate of sputtered material due to ion bombardment. The iron sputter rate was measured versus poisoning ratio from 0.001 to 10. At low poisoning ratios, ion bombardment maintains a dynamically clean surface, sputtering is not suppressed and sputtering rates can be estimated from the literature or from experiments. At poisoning ratios of R p > 0.1 however, the net sputtering rate can be attenuated. The sputter rate of iron in the presence of oxygen at R p > 1 was found to be only 5.4% (0.054) and 11.5% (0.115) of the sputter rate at R p < 0.01 by 300 eV and 600 eV xenon ions, respectively. Although oxygen reduced the iron sputter rate, nitrogen was not found to affect the sputter rate of iron. Nomenclature c contaminant flux (O 2 or N 2 molecules m −2 s −1 ) Xe xenon flux (atoms m −2 s −1

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“…Many experimental and modeling studies have been performed for Hall thruster plumes 43,44,45,46 and also for EP missions beyond GEO. 47,48 The plume of the BPT-4000 thruster has been characterized through detailed diagnostic experiments, 49 materials sputter testing and modeling, 50 and spacecraft-level plume effects modeling. 51 Plume effects depend in part on the specific thruster used but also importantly on the spacecraft configuration.…”

Section: Mission Assurancementioning

confidence: 99%

Evaluation of a 4.5 kW Commercial Hall Thruster System for NASA Science Missions

Hofer¹,

Randolph²,

Oh³

et al. 2006

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

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The readiness of commercial Hall thruster technology is evaluated for near-term use on competitively-award, cost-capped science missions like the NASA Discovery program. Scientists on these programs continue to place higher demands on mission performance that must trade against the cost and performance of propulsion system options. Solar electric propulsion (SEP) systems can provide enabling or enhancing capabilities to several missions, but the widespread and routine use of SEP will only be realized through aggressive cost and schedule risk reduction efforts. Significant cost and schedule risk reductions can potentially be realized with systems based on commercial Hall thruster technology. The abundance of commercial suppliers in the United States and abroad provides a sustainable base from which Hall thruster systems can be cost-effectively obtained through procurements from existing product lines. A Hall thruster propulsion system standard architecture for NASA science missions is proposed. The BPT-4000 from Aerojet is identified as a candidate for near-term use. Differences in qualification requirements between commercial and science missions are identified and a plan is presented for a low-cost, low-risk delta qualification effort. Mission analysis for Discovery-class reference missions are discussed comparing the relative cost and performance benefits of a BPT-4000 based system to an NSTAR ion thruster based system. The BPT-4000 system seems best suited to destinations located relatively close to the sun, inside approximately 2 AU. On a reference near Earth asteroid sample return mission, the BPT-4000 offers mass performance competitive with or superior to NSTAR at much lower cost. Additionally, it is found that a low-cost, mid-power commercial Hall thruster system may be a viable alternative to aerobraking for some missions.Suggestions for the near-and far-term implementation of commercial Hall thrusters on NASA science missions are discussed.

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Validation of Hall thruster plume sputter model

Cited by 8 publications

References 1 publication

SM/MURF: Current Capabilities and Verification as a Replacement of AFRL Plume Simulation Tool COLISEUM

SM/MURF: Current Capabilities and Verification as a Replacement of AFRL Plume Simulation Tool COLISEUM

Influence of residual gases on witness plate measurements during Hall-effect thruster testing

Evaluation of a 4.5 kW Commercial Hall Thruster System for NASA Science Missions

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