The Qualification of a 4.5 kW Hall Thruster Propulsion Subsystem

Fisher, Jack; Wilson, A.; Werthman, Lance

doi:10.2514/6.2003-4551

Cited by 16 publications

(5 citation statements)

References 3 publications

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“…This performance invariance is an indicator of the effectiveness of the HERMeS magnetic shielding topology as previous wear tests performed on nonmagnetically shielded thrusters have observed a decrease in performance during the first approximately 1000 h of operation (Ref. 29). The decrease in performance has been attributed to erosion of the discharge channel walls, which is a phenomenon that is minimized by magnetic shielding (Ref.…”

Section: Performance and Stability Resultssupporting

confidence: 55%

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Long Duration Wear Test of the NASA HERMeS Hall Thruster

Frieman

Kamhawi

Williams

et al. 2018

2018 Joint Propulsion Conference

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Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientifi c and Technical Information (STI) Program plays a key part in helping NASA maintain this important role. The NASA STI Program operates under the auspices of the Agency Chief Information Offi cer. It collects, organizes, provides for archiving, and disseminates NASA's STI. The NASA STI Program provides access to the NASA Technical Report Server-Registered (NTRS Reg) and NASA Technical Report Server-Public (NTRS) thus providing one of the largest collections of aeronautical and space science STI in the world. Results are published in both non-NASA channels and by NASA in the NASA STI Report Series, which includes the following report types: • TECHNICAL PUBLICATION. Reports of completed research or a major signifi cant phase of research that present the results of NASA programs and include extensive data or theoretical analysis. Includes compilations of signifi cant scientifi c and technical data and information deemed to be of continuing reference value. NASA counter-part of peer-reviewed formal professional papers, but has less stringent limitations on manuscript length and extent of graphic presentations.

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Section: Performance and Stability Resultssupporting

confidence: 55%

“…The decrease in performance has been attributed to erosion of the discharge channel walls, which is a phenomenon that is minimized by magnetic shielding (Ref. 29).…”

Section: Performance and Stability Resultsmentioning

confidence: 99%

Long Duration Wear Test of the NASA HERMeS Hall Thruster

Frieman

Kamhawi

Williams

et al. 2018

2018 Joint Propulsion Conference

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“…Hall thruster operation has recently been investigated at discharge voltages and power levels significantly above SOA. Devices which operate at discharge voltages up to 500 Volts are being developed by U.S. industry 24,25 and operation has been characterized at discharge voltages over 1000 Volts. [26][27][28] NASA has developed thrusters which nominally operate at 50 kW, which have been tested at nearly 100 kW.…”

Section: Thermal Characterizationmentioning

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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“…Dual use (both for station-keeping and orbit transfer) thrusters are currently envisioned in industry, such as the BPT-4000 thruster currently undergoing qualification tests at Aerojet [39], a dual-stage Hall thruster [40] and a 5-kW, dual mode Hall thruster at SNECMA. The BPT-4000 operating points are combinations of a discharge power of either 3.0 or 4.5 kW and a discharge voltage of either 300 or 400 V, which yields a maximum thrust of 268 mN (for the orbit transfer mission) and a maximum specified ISP of 1884 s (for the station-keeping mission).…”

Section: Thruster Developmentsmentioning

confidence: 99%

Physical investigations and developments of Hall plasma thrusters

Bouchoule

Boeuf

Héron

et al. 2004

Plasma Phys. Control. Fusion

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Ten years of R&D on Hall plasma thrusters (HPTs) in former USSR led to successful tests in space as early as 1972. Nevertheless, they remain actively investigated within the perspective of a routine use in space technologies. This long story underlines the contrast between a rather simple concept and a complex physical background, up to now not fully understood in a quantitative way. This lack of knowledge limits the development of fully predictive simulation codes. Industrial developments are, nevertheless, under way, with new goals in terms of thruster performances. Illustrations of such developments are given, but this paper is mainly focused on a review of recent results and open questions underlined through a coordinated research programme.

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The Qualification of a 4.5 kW Hall Thruster Propulsion Subsystem

Cited by 16 publications

References 3 publications

Long Duration Wear Test of the NASA HERMeS Hall Thruster

Long Duration Wear Test of the NASA HERMeS Hall Thruster

NASA's 2004 Hall Thruster Program

Physical investigations and developments of Hall plasma thrusters

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