Magnetically enhanced vacuum arc thruster

Keidar, Michael; Schein, J.; Wilson, K.; Gerhan, A.; Au, Michael; Tang, Benjamin; Idzkowski, Luke; Krishnan, M.; Beilis, I. I.

doi:10.1088/0963-0252/14/4/004

Cited by 112 publications

(57 citation statements)

References 39 publications

(74 reference statements)

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“…Was confirmed, that permanent magnet, can improve the characteristics of I bit in about 30 % in level of applied voltage of 800 V. It is can be attributed by the results of Joule heating and cathode material evaporation in this process. 11) Measured characteristics for Horuy-IV VAT, and for the new CFRP propellant, were combined in one table (Table 1). Because of some characteristics were not measured yet, the table is not full.…”

Section: Methods Of Efficiency Improvementmentioning

confidence: 99%

Vacuum Arc Thruster Development and Testing for Micro and Nano Satellites

Aheieva

Toyoda

Cho

2016

AEROSPACE TECHNOLOGY JAPAN

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This paper will describe the development of the Vacuum Arc thruster (VAT) for micro and nano satellites with the main purposes of: attitude control, maintaining orbit-satellite deorbiting. Firstly, this VAT thruster is integrated on-board student microsatellite Horyu-IV, which was developed at the Kyushu Institute of Technology (KIT), Japan. The satellite will be launched in the fiscal year 2015 by H2A rocket. This paper describes the principles of VAT as a direct drive from High Voltage Solar Array (HVSA). Expected performance of this vacuum arc thruster with passive ignition (space plasma condition) was measured. We propose a method for improving the thruster efficiency. Results show that the impulse bit was of the μNs order, and the thrust-56 nN-and efficiency-2.5%-were calculated. Moreover, it was found that the impulse bit changes with the applied voltage. A new CFRP material was developed and used as a cathode for the purpose of improving efficiency. Discharge characteristics of current and the arc rate are presented. Measurements of impulse bit were also done for the VAT in configuration with two different propellants (commercial and new CFRP) and with a permanent magnet of 300 mT.

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Section: Methods Of Efficiency Improvementmentioning

confidence: 99%

Vacuum Arc Thruster Development and Testing for Micro and Nano Satellites

Aheieva

Toyoda

Cho

2016

AEROSPACE TECHNOLOGY JAPAN

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“…The VAT used has a coaxial geometry 115 with an annular anode and a cathode made with different materials placed on an axis. The gap between the anode and cathode is 10 mm.…”

Section: à5mentioning

confidence: 99%

“…115,120,121 A passive feeding system uses a compression spring to feed the cathode to the discharge chamber, where a cathode feeding rate is completely dependent on the erosion profile of the electrode. Compared to a passive system, an active feeding system, which uses a piezoelectric actuator with a spiral spring, can accurately control the feeding rate to achieve uniform erosion of the cathode.…”

Section: Printable Cathode Arc Thrustersmentioning

confidence: 99%

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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262

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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“…Vacuum arc thrusters are similar to PPTs in terms of mechanical design, but initiate a lower power discharge that ablates anode material, and have been specifically developed for low power Nanosatellites [45], [46].…”

Section: ) Electrothermal Accelerationmentioning

confidence: 99%

Space Propulsion Technology for Small Spacecraft

2018

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Abstract-As small satellites become more popular and capable, strategies to provide in-space propulsion increase in importance. Applications range from orbital changes and maintenance, attitude control and desaturation of reaction wheels to drag compensation and de-orbit at spacecraft end-of-life. Space propulsion can be enabled by chemical or electric means, each having different performance and scalability properties. The purpose of this review is to describe the working principles of space propulsion technologies proposed so far for small spacecraft. Given the size, mass, power and operational constraints of small satellites, not all types of propulsion can be used and very few have seen actual implementation in space. Emphasis is given in those strategies that have the potential of miniaturization to be used in all classes of vehicles, down to the popular 1-liter, 1 kg CubeSats and smaller.

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Magnetically enhanced vacuum arc thruster

Cited by 112 publications

References 39 publications

Vacuum Arc Thruster Development and Testing for Micro and Nano Satellites

Vacuum Arc Thruster Development and Testing for Micro and Nano Satellites

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

Space Propulsion Technology for Small Spacecraft

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