Study of electron current extraction from a radio frequency plasma cathode designed as a neutralizer for ion source applications

Jahanbakhsh, Sina; Satir, Mert; Çelik, Murat

doi:10.1063/1.4935015

Cited by 12 publications

(9 citation statements)

References 8 publications

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“…To overcome these application constraints, insert-free plasma cathodes have been introduced in recent years, such as capacitively [3] and inductively [1,2,[4][5][6][7][8][9][10] coupled RF plasma cathodes (CCPCs and ICPCs, respectively), electron-cyclotronresonance cathodes (ECRCs) [11,12], and helicon cathodes [13,14]. The efficiency of an ICPC is better than that of a CCPC or an ECRC under low source power and low volume-flow rate, and the helicon cathode needs a strong magnetic field and high-RF power.…”

Section: Introductionmentioning

confidence: 99%

“…Due to the advantages of ICPCs, several research groups have theoretically investigated inductively coupled radiofrequency plasma neutralizers (RPNs) and conducted a series of experimental studies. All experimental results [1,[4][5][6][7]10] show that the electron-beam current suddenly jumps to a larger value when the bulk plasma is applied with a sufficiently high bias voltage, and a luminous secondary plasma, which is known as an anode spot, is formed at the orifice of the discharge chamber [9]. Formation of an anode spot is the most important feature of RPNs because larger electron beams can be extracted from an RPN after this formation takes place.…”

Section: Introductionmentioning

confidence: 99%

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Study of electron-extraction characteristics of an inductively coupled radio-frequency plasma neutralizer

He¹,

Ma²,

Xue³

2018

Plasma Sci. Technol.

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Inductively coupled radio-frequency (RF) plasma neutralizer (RPN) is an insert-free device that can be employed as an electron source in electric propulsion applications. Electron-extraction characteristics of the RPN are related to the bulk plasma parameters and the device's geometry. Therefore, the effects of different electron-extraction apertures and operational parameters upon the electron-extraction characteristics are investigated according to the global nonambipolar flow and sheath model. Moreover, these models can also be used to explain why the electron-extraction characteristics of the RPN strongly depend upon the formation of the anode spot. During the experimental study, two types of anode spots are observed. Each of them has unique characteristics of electron extraction. Moreover, the hysteresis of an anode spot is observed by changing the xenon volume-flow rates or the bias voltages. In addition, the rapid ignited method, gas-utilization factor, electron-extraction cost and other factors that need to be considered in the design of the RPN are also discussed.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Study of electron-extraction characteristics of an inductively coupled radio-frequency plasma neutralizer

He¹,

Ma²,

Xue³

2018

Plasma Sci. Technol.

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“…4 As a consequence, alternative neutralizers, which do not rely on hot emissive materials and thus are not affected by cathode poisoning, have been receiving much attention from the research community. 5,6 The aim of this study is to develop a low-power neutralizer based on a discharge in crossed E × B fields, rather than on thermionic emissive materials. In addition, future plans include neutralizer optimization in order to enhance its operability with high impurity rates in the feed gas and, ultimately, with molecular, reactive propellants.…”

Section: Introductionmentioning

confidence: 99%

Experimental Performance Characterization of a Novel Direct Current Cold Cathode Neutralizer for Electric Thruster Applications

Gurciullo¹,

Knoll²

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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The performance of a novel neutralizer for space applications based on a E × B discharge is presented. Preliminary tests were carried out with argon gas and flow rates in the range of 5-10 SCCM. Electrons were extracted through an orifice of diameter 1.8 mm. The maximum extracted current versus input power reported was 2.4 mA/W. The total power input, given by the sum of discharge power plus the extraction power, was in the range of 40-90 W. During extraction tests, the discharge current was limited at 0.2 A due to limit in the cooling system. Future work will be focused on tests at various extraction orifice diameters and cathode materials. Ultimately, xenon and non-conventional gases would be tested as working gases. Nomenclature αExtraction efficiency B Magnetic field density E Electric field H Energy efficiency parameter, given by extracted current versus input power I cathode Cathode current, or discharge current I collector Collector current, or electron extraction current P cathode Power supplied to the cathode, or discharge power P collector Power supplied to the collector, or extraction power

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“…128 In RF cathodes, the energy source, i.e., the antenna, does not come into contact with plasma, which can avoid potential issues with the discharge cathode life. 129 However, these cathodes are characterized by an electron-extraction-cost of over 100 W/A, making them energy-costly.…”

Section: Overview Of Cathode Techniques For L-propulsionmentioning

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

267

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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Study of electron current extraction from a radio frequency plasma cathode designed as a neutralizer for ion source applications

Cited by 12 publications

References 8 publications

Study of electron-extraction characteristics of an inductively coupled radio-frequency plasma neutralizer

Study of electron-extraction characteristics of an inductively coupled radio-frequency plasma neutralizer

Experimental Performance Characterization of a Novel Direct Current Cold Cathode Neutralizer for Electric Thruster Applications

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

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