A study of cylindrical Hall thruster for low power space applications

Raitses, Yevgeny; Fisch, Nathaniel J.; Ertmer, Kevin M.; Burlingame, C. Andrew

doi:10.2514/6.2000-3421

Cited by 10 publications

(5 citation statements)

References 13 publications

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“…Raitses et al [16] developed a cylindrical Hall thruster (CHT), combining the conventional annular design with the simplicity and enhanced volume-to-surface-area ratio of the end-Hall thruster (EHT). The CHT channel features an annular region near the anode, followed by a cylindrical region.…”

mentioning

confidence: 99%

Ionization, Plume Properties, and Performance of Cylindrical Hall Thrusters

Diamant

Pollard

Raitses

et al. 2010

IEEE Trans. Plasma Sci.

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It is shown experimentally that the cylindrical Hall thruster (CHT) produces a highly ionized plasma flow with mass utilization efficiencies greater than 100% due to generation of multicharged ions. For the CHT employing geometries with and without a short annular section, used to enhance ionization, plume divergence reductions of approximately 25% were demonstrated by running a cathode-keeper discharge along with the main cathode-anode discharge. Thruster anode efficiencies varied from approximately 15% to 35% over input powers from 70 to 220 W. A 2-A keeper discharge resulted in an approximately 20% increase in anode specific impulse for both geometries, and the specific impulse for the case of no annular section was, on average, 13% higher than that with the annular section. The multicharged ion fraction increased with keeper current, and the quantity of channel erosion products in the plume was correlated with that of multicharged ions.

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mentioning

confidence: 99%

Ionization, Plume Properties, and Performance of Cylindrical Hall Thrusters

Diamant

Pollard

Raitses

et al. 2010

IEEE Trans. Plasma Sci.

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“…It is important to note that Hall thrusters operating at power levels below 500 W are currently not available but are in the research phase of development (c.f. [10,11]…”

Section: Discussionmentioning

confidence: 99%

Plasma propulsion for three terrestrial planet finder architectures - Free-flying, monolithic and tethered

Polzin

Choueiri²,

Gurfil

et al. 2001

37th Joint Propulsion Conference and Exhibit

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A systems-level trade-off study is presented comparing the propulsion requirements and associated final masses for different architectural implementations of the Terrestrial Planet Finder (TPF) mission. The study focuses on the mN-level propulsion chores associated with rotation and repointing. Three interferometer configurations; free-flying, monolithic and tethered; lead to estimates of power requirements and spacecraft masses associated with different plasma propulsion systems required to maneuver the interferometer throughout its lifetime. The parametric study includes the following plasma propulsion options: Hall thruster, Field Emission Electric Propulsion (FEEP), Ablative Pulsed Plasma Thruster (APPT), Ablative Z-pinch Pulsed Plasma Thruster (AZPPT) and Gas-Fed Pulsed Plasma Thruster (GF-PPT). For the different thruster and architecture combinations, it is found that the initial mass for a system falls between 3200 and 4200 kg. Also, in general, for a given architecture, the tether has the lowest initial mass followed by the free flyer and the monolith. Finally, the initial mass was found not to be particularly sensitive to the type of plasma propulsion system so the choice should be made based on technological readiness, systems integration considerations and spacecraft contamination issues associated with the chosen system. 'Graduate Student, Electric Propulsion & Plasma Dynamics Lab (EPPDyL). Applied Physics Group. Member AIAA.

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“…These findings have shown that the spectral response of the plasma depends on the position inside the thruster, ion mass and density, ion-accelerating discharge voltage, channel geometry, and the magnetic field gradient and magnitude. All of this prior thruster research in the realm of plasma-thruster instabilities has focused on the relationship of these modes to various discharge settings [7][8][9][10][11][12][13][14][15] and thruster geometries [16][17] . While the use of active feedback control for mitigating these instabilities has been suggested in the past 9,10 , there has yet to be an actively controlled Hall thruster in closed loop at frequencies near the dominant breathing mode.…”

Section: B Plasma Instabilities and Oscillatory Modesmentioning

confidence: 99%

Evaluation and Active Control of Clustered Hall Thruster Discharge Oscillations

Lobbia¹,

Gallimore²

2005

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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While preliminary experiments with a cluster of four Busek 200-Watt (BHT-200-X3) Closed Drift Hall thrusters indicate reasonable performance scalability from single thruster experiments, cluster plume interactions are believed to give rise to an increased ion energy spectrum as well as cross-talk and synchronization between the thruster discharges. Recent experiments with a higher power cluster of four 600-Watt (BHT-600) Hall thrusters have exhibited similar clustering behavior. Discharge voltage and current characteristics are studied in detail with frequency magnitude and phase analysis from low frequencies up to 100 kHz. Modulation of the electromagnetic circuit current provides data for the analysis of multiple correlations between the various signals, thereby quantifying all interdependencies. Accentuation and shifting of various modal features (including the so called "breathing" mode) are observed in the clustered configuration. We are then motivated to provide active stabilization of the observed oscillations in an effort to improve thruster lifetimes, overall efficiency, and performance. After identification of the thruster cluster system, various models and control algorithms are developed to provide stabilizing feedback control to the clustered Hall thrusters. Application of this control in real time has shown reductions in the discharge oscillations during thruster startup and steady operation.

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A study of cylindrical Hall thruster for low power space applications

Cited by 10 publications

References 13 publications

Ionization, Plume Properties, and Performance of Cylindrical Hall Thrusters

Ionization, Plume Properties, and Performance of Cylindrical Hall Thrusters

Plasma propulsion for three terrestrial planet finder architectures - Free-flying, monolithic and tethered

Evaluation and Active Control of Clustered Hall Thruster Discharge Oscillations

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