A Commercial One Newton Hall Effect Thruster for High Power In-Space Missions

Szabo, James; Pote, Bruce; Hruby, V.; Byrne, Lawrence; Tadrake, Rachel; Kolencik, George; Kamhawi, Hani; Haag, Thomas

doi:10.2514/6.2011-6152

Cited by 12 publications

(9 citation statements)

References 15 publications

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“…Indeed, the Hall thruster technology [3] is already in use for satellite maneuvers, station-keeping, and large constellations [4]. Additionally, the developments of spacecraft power generation and management systems in recent years have augmented the available on-board power, which can be used to supply high-power Hall thrusters [5] Over the last four decades, several high-power Hall thruster prototypes with nominal discharge powers higher than 10 kW have been developed and tested [6][7][8][9][10][11][12][13][14][15]. However, the complete development of such devices relies on the possibility of their testing in adequate on-ground vacuum facilities with proper pumping speed and dimensions.…”

Section: Introductionmentioning

confidence: 99%

Background Pressure Effects on the Performance of a 20 kW Magnetically Shielded Hall Thruster Operating in Various Configurations

et al. 2021

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The paper reports the characterization results of a 20 kW-class magnetically shielded Hall thruster in three different configurations and operating with a centrally mounted cathode. The characterization was carried out at two different pumping speeds in SITAEL’s IV10 vacuum chamber, resulting in two different background pressure levels for each tested operating point. A linear behavior of discharge current and thrust values versus the anode mass flow rate was noticed for both pumping speeds levels and for all the three configurations. In addition, the thrust and discharge current values were always found to be lower at lower background pressure levels. From the performance levels, a preliminary estimate of the ingested mass flow rates was performed, and the values were then compared to a recently developed background flow model. The results suggested that, for this thruster and in the tested operating regimes, the change in performance due to background pressure could be ascribed not only to the ingestion of external mass flow coming from the chamber but also to other physical processes caused by the flux of residual background neutrals.

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Section: Introductionmentioning

confidence: 99%

Background Pressure Effects on the Performance of a 20 kW Magnetically Shielded Hall Thruster Operating in Various Configurations

et al. 2021

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“…24,25 Since then NASA GRC has been involved with testing and/or design of numerous high power Hall thrusters that include the NASA-457Mv1 (50 kW), NASA-400M (40 kW), NASA-300M (20 kW), NASA-457Mv2 (50 kW), Busek's BHT-20k, and Aerojet-Rockedyne's XR-12. 26,27,28,29,3031,32,33,34,35,36 NASA GRC's and JPL's extensive experience with performance testing, and ion (gridded and non-gridded) thrusters near and far-field plasma measurements is being leveraged in support of the development of a long-life high-performing Hall thruster for NASA's SEP TDM.…”

Section: Design Specifications Of the 125-kw Technology Development mentioning

confidence: 99%

Overview of the Development of the Solar Electric Propulsion Technology Demonstration Mission 12.5-kW Hall Thruster

Kamhawi

Huang²,

Haag³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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NASA is developing mission concepts for a solar electric propulsion technology demonstration mission. A number of mission concepts are being evaluated including ambitious missions to near Earth objects. The demonstration of a high-power solar electric propulsion capability is one of the objectives of the candidate missions under consideration. In support of NASA's exploration goals, a number of projects are developing extensible technologies to support NASA's near and long term mission needs. Specifically, the Space Technology Mission Directorate Solar Electric Propulsion Technology Demonstration Mission project is funding the development of a 12.5-kW magnetically shielded Hall thruster system to support future NASA missions. This paper presents the design attributes of the thruster that was collaboratively developed by the NASA Glenn Research Center and the Jet Propulsion Laboratory. The paper provides an overview of the magnetic, plasma, thermal, and structural modeling activities that were carried out in support of the thruster design. The paper also summarizes the results of the functional tests that have been carried out to date. The planned thruster performance, plasma diagnostics (internal and in the plume), thermal, wear, and mechanical tests are outlined. AbbreviationsAFRL = Air Force Research Laboratory ARRM = Asteroid Retrieval and Redirect Mission GRC = Glenn Research Center HEFT = Human Exploration Framework Team HEOMD = Human Exploration and Operations Mission Directorate JPL = Jet Propulsion Laboratory MS = Magnetically Shielded

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“…This technique, which has origins in the Russian literature, 10 was first explored experimentally in two 10-kW class thrusters. 11,12,13,14 Following the successful development of low-power NHTs, a 100-kW class thruster 15,16,17,18 known as the X3 was developed by the University of Michigan, the Air Force Research Laboratory, NASA, and ElectroDynamic Applications. The X3 is designed to be capable of operation from 300-800 V discharge voltage and 2-200 kW discharge power.…”

mentioning

confidence: 99%