Efficiency Analysis of a High-Specific Impulse Hall Thruster

Hofer, Richard R.; Gallimore, Alec D.

doi:10.2514/6.2004-3602

Cited by 65 publications

(34 citation statements)

References 35 publications

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“…FY04 efforts investigated krypton Hall thruster operation through a performance and plasma characterization of the 5 kW NASA-173M V2 Hall thruster, which has previously demonstrated both high-efficiency and highspecific impulse operation on xenon. 20,21 Analysis has shown that efficient operation of the NASA-173Mv2 on xenon was enabled through regulation of the electron current with the magnetic field. 21 P l u m e diagnostics including a Faraday probe, RPA, and an ExB probe are being used to quantify the differences in xenon and krypton plasma parameters.…”

Section: Krypton Hallmentioning

confidence: 99%

NASA's 2004 Hall Thruster Program

Jacobson

Manzella

Hofer³

et al. 2004

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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An overview of NASA's Hall thruster research and development tasks conducted during fiscal year 2004 is presented. These tasks focus on: raising the technology readiness level of high power Hall thrusters, developing a moderatepower/moderate specific impulse Hall thruster, demonstrating high-power/high specific impulse Hall thruster operation, and addressing the fundamental technical challenges of emerging Hall thruster concepts. Programmatic background information, technical accomplishments and out year plans for each program element performed under the sponsorship of the In-Space Transportation Program, Project Prometheus and the Energetics Project are provided.

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Section: Krypton Hallmentioning

confidence: 99%

NASA's 2004 Hall Thruster Program

Jacobson

Manzella

Hofer³

et al. 2004

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Self Cite

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“…For higher discharge voltages, f i Q is nearly unity meaning complete single ionization of the propellant. 7 In low voltage operation propellant ionization drops and f i decreases. The calculation of current efficiency measurements in figure 3 do not include the ionization charge quantity.…”

Section: Equipmentmentioning

confidence: 99%

Energy Efficiency in Low Voltage Hall Thrusters

Ross¹,

King²

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Energy efficiency measurements were taken on a 2 kW (nominal) Hall thruster operating at discharge voltages of 100-200 V and 3 mg/s of xenon. Acceleration and current efficiencies were compared to thrust efficiency over a range of magnet coil current values of 0 A -2.5 A. Acceleration efficiencies were obtained with a 4-grid Retarding potential analyzer and current efficiency measurements were calculated from the discharge current as read from the power supply maintaining the anodecathode potential. The acceleration efficiency and current efficiency were divergent in the region of maximum thrust efficiency. Acceleration efficiency increased with decreasing magnet current where the cathode-to-ground potential was determined to account for a portion of the increase in the region of interest. Nomenclaturė

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“…The term Thrust Efficiency has been used by Kim 1 but also appears under the name anode efficiency 14 and discharge efficiency 5 and refers to a benchmark for anode performance that excludes the magnets and cathode operation. Figure 2 shows the thruster operated at above 50% thrust efficiency for all three mass flow rates at 300 V. The data here is comparable with the data from reference 9 after the cathode operation is accounted for.…”

Section: Efficiency Analysismentioning

confidence: 99%

Efficiency Analysis of a Low Discharge Voltage Hall Thruster

Ross¹,

Sommerville²,

King³

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Power loss mechanisms for a 2 kW (nominal) Hall thruster operating at low discharge voltages were examined through thrust stand measurements and probe studies. Operating conditions included discharge voltages ranging from 100 V to 300 V and mass flow rates of 3 to 5 mg/s of xenon. Thrust stand measurements indicate a minimum thrust efficiency of 15% at 100 V at 3 mg/s and a maximum of 59% at 300 V and 5 mg/s. Retarding potential analyzer, emissive and Faraday probes were utilized to quantify multiple sources of inefficiency. The ratio of exhausted ion current to discharge current was found to be the dominant loss mechanism at low discharge voltage.

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Efficiency Analysis of a High-Specific Impulse Hall Thruster

Cited by 65 publications

References 35 publications

NASA's 2004 Hall Thruster Program

NASA's 2004 Hall Thruster Program

Energy Efficiency in Low Voltage Hall Thrusters

Efficiency Analysis of a Low Discharge Voltage Hall Thruster

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