A study of cylindrical Hall thruster for low power space applications

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

doi:10.2172/759246

Cited by 4 publications

(1 citation statement)

References 7 publications

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“…The short annular channel is used to maintain high propellant utilization efficiency in the CHT [3], [4]. On the other hand, the absence of the annular channel may be advantageous with respect to the thruster lifetime [5], [6].…”

Section: Introductionmentioning

confidence: 99%

Simulations of a Miniaturized Cylindrical Hall Thruster

Garrigues

Hagelaar

Boeuf

et al. 2008

IEEE Trans. Plasma Sci.

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A miniaturized cylindrical Hall thruster (CHT) is studied using a 2-D hybrid model. The simulation results are compared with experimental results for 100-W laboratory CHT. The channel of this thruster has a short coaxial part and a longer cylindrical region with a larger volume-to-surface ratio to reduce erosion. The 2-D model combines a fluid description of the electrons (continuity and momentum equations) and a particle description of the ions and the neutral atoms. The simulations confirm that the ionization takes place in the annular part of the channel, while the unusually high propellant utilization efficiency is found to be due to doubly charged ions.

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Section: Introductionmentioning

confidence: 99%

Simulations of a Miniaturized Cylindrical Hall Thruster

Garrigues

Hagelaar

Boeuf

et al. 2008

IEEE Trans. Plasma Sci.

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Far-field plume characterization of a low-power cylindrical Hall thruster

Perrotin,

Vinci,

Mazouffre

et al. 2024

Journal of Applied Physics

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A fully cylindrical Hall thruster prototype was tested in the power range of 30–300 W with the objective of understanding the behavior of the discharge as a function of input parameters. Various operating conditions were compared, including two magnetic field configurations, a set of propellant mass flow rates, and a range of discharge voltages. Plasma properties were measured in the plume, with a Langmuir probe, a retarding potential analyzer, and a Faraday cup. The experimental results showed that the mass flow rate strongly affects the ionization and, consequently, other related properties such as the plasma density, currents, and propellant utilization. The discharge voltage also appeared to influence the ion energy and propellant utilization. The performance accessible from the measured magnitudes is assessed, resulting in a maximum thrust efficiency of about 18% at 0.35 mg s−1 and 168 W.

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Overview of U.S. academic programs in electric propulsion

Gatsonis

Martı́nez-Sánchez

2000

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Graduate-level research in electric propulsion has been a staple of aerospace engineering and mechanical engineering advanced degree programs for about 40 years. These programs have brought to the field an important fundamental research component to balance contributions from government and industry laboratories. The research has historically covered just about every type of electric thruster ever considered, but over the last few years has begun to focus only on efficient, low mass electric propulsion systems with a strong potential for spaceflight applications. Historically, research activities in electric propulsion are typically recorded as AIAA preprints and as articles in the AIAA Journal of Propulsion and Power. A significant number of articles are also published in the AIAA Journal of Thermophysics and Heat Transfer, the Journal of Spacecraft and Rockets, the AIAA Journal, and the journals of the IEEE. Additional important sources are the papers published in the proceedings of the biannual International Electric Propulsion Conference. These proceedings are available from the Electric Rocket Propulsion Society in the form of either hardcopy or CD-ROM. Many graduates of electric propulsion programs have remained in the field. The authors listed above include several current research investigators who earned their degrees in the 1960's and early 1970's. Many of today's graduates are also remaining in the electric propulsion research arena in industry, government, and academia.

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A study of cylindrical Hall thruster for low power space applications

Cited by 4 publications

References 7 publications

Simulations of a Miniaturized Cylindrical Hall Thruster

Simulations of a Miniaturized Cylindrical Hall Thruster

Far-field plume characterization of a low-power cylindrical Hall thruster

Overview of U.S. academic programs in electric propulsion

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