Performance Characteristics of Micro-cathode Arc Thruster

Zhuang, Taisen; Shashurin, Alexey; Denz, Thomas; Keidar, Michael; Vail, P. J.; Pancotti, Anthony

doi:10.2514/1.b34567

Cited by 45 publications

(21 citation statements)

References 11 publications

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“…These thruster configurations are shown schematically in Figure 1. It is well known that addition of external magnetic field can improve VAT performance [8,9] and the micro-cathode VAT [10,11], a ring shaped device, is a well studied case. However, for a magnetically enhanced coaxial VAT, only limited results are documented in the literature [12].…”

Section: Introductionmentioning

confidence: 99%

Characterization of Vacuum Arc Thruster Performance in Weak Magnetic Nozzle

Chowdhury

Kronhaus

2020

Aerospace

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Vacuum arc thruster performance in a magnetic nozzle configuration is experimentally characterized. Measurements are performed on a miniature coaxial thruster with an anode inner diameter of 1.8 mm. The magnetic field B is produced by a single air coil, 18 mm in diameter. Direct measurement of thrust, mass consumption and arc current are performed. To obtain statistically viable results ≈ 6000 arc pulses are analyzed at each operational point. Cathode mass erosion is measured using laser profilometry. To sustain thruster operation over several measurement cycles, an active cathode feeding system is used. For 0 < B ≤ 0.2 T, performance increase over the non-magnetic case is observed with the best thrust to arc power ratio T / P ≈ 9 μ N/W obtained at B ≈ 0.2 T. A parametric model is provided that captures the performance enhancement based on beam collimation and acceleration by the magnetic nozzle. For B > 0.2 T, the arc discharge is shown to be suppressed nullifying any additional gains by the nozzle effect.

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Section: Introductionmentioning

confidence: 99%

Characterization of Vacuum Arc Thruster Performance in Weak Magnetic Nozzle

Chowdhury

Kronhaus

2020

Aerospace

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“…In addition, a magnetic field augmentation leads to an increase in cathode mass consumption rate by a factor of 5 that lead to enhanced impulse bit. [1][2][3][4][5][6] Another important contributor to thrust is the ion velocity.…”

Section: Introductionmentioning

confidence: 99%

Ion velocities in a micro-cathode arc thruster

et al. 2012

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“…71,72 This thruster improves on the vacuum arc discharge thruster by applying a specially designed external magnetic field. 73 The unique magnetic field conditions achieved in a vacuum arc offer several potential advantages in these devices.…”

Section: Micro-cathode Arc Thrusters For Cubesat Propulsionmentioning

confidence: 99%

“…The thrust measurement with a different strength of the magnetic field has been described and discussed elsewhere. 71 The average impulse bit increases from about 0.1 lN-s at zero magnetic field to up to about 1.15 lN-s in the case of 0.3 T magnetic field. Thus, it can be concluded that the impulse bit increases tenfold when the magnetic field is applied.…”

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confidence: 93%

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

Levchenko

Bazaka

Ding

et al. 2018

Applied Physics Reviews

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271

104

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Rapid evolution of miniaturized, automatic, robotized, function-centered devices has redefined space technology, bringing closer the realization of most ambitious interplanetary missions and intense near-Earth space exploration. Small unmanned satellites and probes are now being launched in hundreds at a time, resurrecting a dream of satellite constellations, i.e., wide, all-covering networks of small satellites capable of forming universal multifunctional, intelligent platforms for global communication, navigation, ubiquitous data mining, Earth observation, and many other functions, which was once doomed by the extraordinary cost of such systems. The ingression of novel nanostructured materials provided a solid base that enabled the advancement of these affordable systems in aspects of power, instrumentation, and communication. However, absence of efficient and reliable thrust systems with the capacity to support precise maneuvering of small satellites and CubeSats over long periods of deployment remains a real stumbling block both for the deployment of large satellite systems and for further exploration of deep space using a new generation of spacecraft. The last few years have seen tremendous global efforts to develop various miniaturized space thrusters, with great success stories. Yet, there are critical challenges that still face the space technology. These have been outlined at an inaugural International Workshop on Micropropulsion and Cubesats, MPCS-2017, a joint effort between Plasma Sources and Application Centre/Space Propulsion Centre (Singapore) and the Micropropulsion and Nanotechnology Lab, the G. Washington University (USA) devoted to miniaturized space propulsion systems, and hosted by CNR-Nanotec—P.Las.M.I. lab in Bari, Italy. This focused review aims to highlight the most promising developments reported at MPCS-2017 by leading world-reputed experts in miniaturized space propulsion systems. Recent advances in several major types of small thrusters including Hall thrusters, ion engines, helicon, and vacuum arc devices are presented, and trends and perspectives are outlined.

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Performance Characteristics of Micro-cathode Arc Thruster

Cited by 45 publications

References 11 publications

Characterization of Vacuum Arc Thruster Performance in Weak Magnetic Nozzle

Characterization of Vacuum Arc Thruster Performance in Weak Magnetic Nozzle

Ion velocities in a micro-cathode arc thruster

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

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