Open Access
Performance and Plume Characterization of a Helicon Hall Thruster
TLDR
The work done to date on the HHT performance evaluation for input power from 0.6 to 8 kW with discharge voltages ranging from 100 to 600 V and discharge currents ranging from 5 to 25 A as mentioned in this paper.Abstract:
The Helicon Hall Thruster (HHT) development program seeks to achieve high efficiency operation of a high-thrust, low-specific impulse (Isp) Hall thruster by employing the efficient ionization mechanism of a helicon source while maintaining the efficient acceleration characteristics which have made Hall thrusters an attractive propulsion option. In the HHT, ions are created in an annular helicon first stage and then accelerated in a closed-drift, Hall-effect second stage. Helicon waves, which are cylindrically bounded whistler waves, are considered to be one of the most efficient methods of producing a high-density, low-temperature plasma. A decrease in the power required for propellant ionization will directly translate into an increase in thruster efficiency at non-nominal Hall thruster operating conditions. This paper will present the work done to date on the HHT performance evaluation for input power from 0.6 to 8 kW with discharge voltages ranging from 100 to 600 V and discharge currents ranging from 5 to 25 A. Results of the performance characterizations suggest that there is a possible advantage of a Hall thruster with RF ionization stage at increasing RF-power.read more
Citations
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Journal ArticleDOI
A review of research in low earth orbit propellant collection
TL;DR: A comprehensive review examines the efforts of previous researchers to develop concepts for propellant-collecting spacecraft, estimate the performance of these systems, and understand the physics involved as mentioned in this paper, and outlines five areas for continued research These areas include air compatible cathode technology, techniques to improve propellant utilization on atmospheric species, in-space compressor and liquefaction technology, improved hypersonic and hyperthermal free molecular flow inlet designs, and improved understanding of how design parameters affect system performance.
Journal ArticleDOI
Performance of a Helicon Hall Thruster Operating with Xenon, Argon, and Nitrogen
TL;DR: The helicon Hall thruster is a two-stage thruster that was developed to investigate whether a radio frequency ionization stage can improve the overall efficiency of the Hall thrusters operating at high thrust and low specific impulse as discussed by the authors.
ReportDOI
Variable operation of Hall thruster with multiple segmented electrodes
TL;DR: In this article, a variable plasma jet velocity with low beam divergence over a range of mass flow rates can be achieved through segmented electrode operation of Hall plasma accelerator, at some cost in efficiency.
Journal ArticleDOI
Plume Characterization of an Ion Focusing Hall Thruster
TL;DR: The T-220HT is a 10-kW class Hall effect thruster developed as the primary propulsion system for satellites as mentioned in this paper, where electrically-biased graphite electrode rings are embedded in the discharge channel walls to repel radial ions.
Journal ArticleDOI
Propellant Thermal Management Effect on Neutral Residence Time in Low-Voltage Hall Thrusters
TL;DR: In this paper, the authors investigated the effect of anode temperature on the performance of a 4.5-kW Hall-effect thruster and showed that discharge current on the anode band, which is upstream of the bulk Hall current region, generates a 10% increase in ion current density at the thruster centerline for discharge voltages of 100, 125, and 150 V at a xenon mass flow rate of 5.
References
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Journal ArticleDOI
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Proceedings ArticleDOI
Laboratory Model 50 kW Hall Thruster
TL;DR: A 0.46 meter diameter Hall thruster was fabricated and performance tested at powers up to 72 kilowatts as discussed by the authors, with discharge specific impulses ranging from 1750 to 3250 seconds with discharge efficiencies between 46 and 65 percent.