Development status of the BPT family of Hall Thruster systems

Wilson, Frank T.; King, D. Q.; Willey, M.; Aadland, Randy; Tilley, Dennis L.; Grys, Kristi de

doi:10.2514/6.1999-2573

Cited by 5 publications

(4 citation statements)

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“…14,16,19,20), a detailed spacecraft application was not shown. The following section examines two types of contamination deposition: eroded thruster products and sputtered spacecraft materials.…”

Section: 2mentioning

confidence: 98%

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<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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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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Section: 2mentioning

confidence: 98%

“…Figure 2 compares the simulated and experimental (from Ref. 16) ion current density at 60 cm as a function of angle from the plume centerline. Results of this preliminary model correlation to the test data are considered to be fairly good for the first attempt.…”

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 Hall-effect thruster used for this work was a 2-kW-class thruster similar to an Aerojet BPT-2000. [21][22][23][24][25] The outer diameter of the thruster body is 120 mm and the channel width is 13 mm. Nominal power input is 2200 W at 350 V, which yields a specific impulse of 1765 s (operating on xenon) with approximately 50% efficiency.…”

Section: Experimental Apparatusmentioning

confidence: 99%

Application of maximum likelihood methods to laser Thomson scattering measurements of low density plasmas

Washeleski

Meyer

King

2013

Review of Scientific Instruments

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Laser Thomson scattering (LTS) is an established plasma diagnostic technique that has seen recent application to low density plasmas. It is difficult to perform LTS measurements when the scattered signal is weak as a result of low electron number density, poor optical access to the plasma, or both. Photon counting methods are often implemented in order to perform measurements in these low signal conditions. However, photon counting measurements performed with photo-multiplier tubes are time consuming and multi-photon arrivals are incorrectly recorded. In order to overcome these shortcomings a new data analysis method based on maximum likelihood estimation was developed. The key feature of this new data processing method is the inclusion of non-arrival events in determining the scattered Thomson signal. Maximum likelihood estimation and its application to Thomson scattering at low signal levels is presented and application of the new processing method to LTS measurements performed in the plume of a 2-kW Hall-effect thruster is discussed.

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“…The Hall thruster used for this work was a 2-kW-class thruster similar to an Aerojet BPT-2000 [68][69][70][71][72]. The outer diameter of the thruster body is 120 mm and the channel width is 13 mm.…”

Section: Thrustermentioning

confidence: 99%

Laser Thomson scattering measurements of electron temperature and density in a Hall-effect plasma

Washeleski¹

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Development status of the BPT family of Hall Thruster systems

Cited by 5 publications

References 0 publications

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

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

Application of maximum likelihood methods to laser Thomson scattering measurements of low density plasmas

Laser Thomson scattering measurements of electron temperature and density in a Hall-effect plasma

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