Micro-Vacuum Arc Thruster with Extended Lifetime

Zhuang, Taisen; Shashurin, Alexey; Denz, Thomas; Chichka, David; Keidar, Michael

doi:10.2514/6.2009-4820

Cited by 18 publications

(10 citation statements)

References 3 publications

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“…It was observed that application of magnetic field changes plasma plume behavior drastically. Indeed, one can see that the plume, indicating that the magnetic field increases the plasma output, which is consistent with previous results [3], [4], [6]. In order to characterize the plasma plume response on the magnetic field in details, we measured the spatial distribution of plasma by means of a set of concentric circular Langmuir probes, as shown in Fig.…”

Section: Microcathode Thruster (µCt) Plume Characterizationsupporting

confidence: 80%

Microcathode Thruster $(\mu\hbox{CT})$ Plume Characterization

Zhuang

Shashurin

Keidar

2011

IEEE Trans. Plasma Sci.

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An experimental observation of microcathode thruster plasma plume is described. An effect of the magnetic field on the plume expansion is considered. Two observation techniques are employed--charge-coupled-device camera and the concentric Langmuir probe. It is found that magnetic field significantly affects the plasma plume, and the strong magnetic field can lead to hollow plume formation.Index Terms-Magnetic field enhance, plasma plume, thruster. M ICROCATHODE thruster (µCT) has been proposed to address the long-time operation of the microthrusters for nanosatellite propulsion [1]. Previously, it has been shown that, the µCT significantly improves efficiency and reduces propulsion system mass by utilizing inductive energy storage in the power processing unit [2]- [4]. The µCT employs a magnetic field produced by a coil placed around the anode of the thruster. Magnetic field leads to a high ly directional plasma plume, creates a rotating cathode arc-spot (well known as J × B [5]), and increases the operational lifetime of the thruster. The objective of this paper is to visualize the difference between the exhaust plasma plume with and without magnetic field. Two methods are used, namely, photographing the plume and ion current measurementsThe µCT plasma plume was photographed by a chargecoupled device (CCD) camera (Nikon D90 was used) placed on the side window of the chamber about 20 cm away from the thruster axis line. The Nikkor zoom lens 18-55 mm F/3.5-5.6 was used. The camera explosion time was set up to be 20 s and the CCD detector sensitivity International Organization for Standardization to 1600. The thruster and camera were placed in the dark room to decrease the noise, which is caused by the camera's high sensitivity. The µCT working frequency was 0.5 Hz, which means that the camera accumulated ten discharge pulses in one image. Fig. 1 shows the plume images without and with (0.266 T) magnetic field (the blue arrow in the lower image indicates axes for both thruster and magnetic coil, and the yellow lines indicate magnetic field distribution simulated by Finite Element Method Magnetics (FEMM) software). It was observed that application of magnetic field changes plasma plume behavior drastically. Indeed, one can see that the Manuscript Fig. 1. CCD camera images of the plasma plume (upper) without and (lower) with magnetic field (B = 0.266 T). (Yellow lines) Magnetic field distribution and (blue arrow) the central axes for both magnetic coil and thruster.Fig. 2. Schematic of the thruster and experimental setup of concentric circular probes.magnetic field collimates the plasma plume. In addition, while comparing the upper and lower images, it can be noted that the magnetic field significantly increases the brightness of the 0093-3813/$26.00

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Section: Microcathode Thruster (µCt) Plume Characterizationsupporting

confidence: 80%

Microcathode Thruster $(\mu\hbox{CT})$ Plume Characterization

Zhuang

Shashurin

Keidar

2011

IEEE Trans. Plasma Sci.

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“…Most vacuum arc studies in literature generally use the ion current peak to determine the ICDD from a vacuum arc [3], [11], [12], [16]. However, there are some disadvantages with this approach.…”

Section: A Ion Charge Measurementmentioning

confidence: 99%

“…Previous measurements of the ICDD of a VAT plume have been taken about a single axis of rotation [3], along a single plane [11], and concentrically [12]. However, variation in the cathode spots' average location on the cathode surface may result in an ICDD profile deviating from the thruster's normal axis.…”

Section: B Icdd Capture Systemmentioning

confidence: 99%

Influence of Cathode Shape on Vacuum Arc Thruster Performance and Operation

Lun

Law

2015

IEEE Trans. Plasma Sci.

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Vacuum arc thrusters (VATs) are a potentially useful technology for use as microthrusters, given their simplicity, low mass, and low-power requirements. However, further development is still needed to improve and mature their performance and operation. In an effort to improve thruster characteristics, we investigate the use of conically shaped convergent cathode surface profiles in a low-power coaxial VAT design. Experimental measurements of ion current density distribution, thrust, and erosion rate were taken for a range of cathode profiles and materials. Results show that modifying the profile of the cathode face can affect the plasma jet's plume distribution and even improve thrust production in certain cases. One likely cause of the thrust improvement is speculated to be increased charge exchange collisions resulting in a lower average ion charge state of the ejecting plasma.Index Terms-Cathode, diagnostics, ion charge state, ion current density distribution (ICDD), microthruster, plasma jet, propulsion, pulsed power, thrust stand, vacuum arc thruster (VAT).

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“…Micro-Cathode Arc thruster (µCAT) based on a magnetically enhanced vacuum arc has been studied and its advantages for the control of nanosatellites were demonstrated 1 , 2 . In previous work 2 it is found that the magnetic field leads to cathode spot motion in the azimuthal direction, well-known as-J × B 3 , which causing uniform erosion of the cathode material. However, in order to better understand its potential, the µCAT requires detailed characterization, which is the objective of this work.…”

Section: Introductionmentioning

confidence: 99%

Performance characterization of the micro-Cathode Arc Thruster and propulsion system for space applications

Zhuang¹,

Shashurin²,

Haque³

et al. 2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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This paper describes a further development and characterization of vacuum arc thruster with external magnetic field. The velocity of ions moving from the micro-Cathode Arc Thrusters (µCAT) cathode spots was measured using a set of grid probes along the path of the plasma plume expansion. The goal was to get the ion drift velocity and determine how much, if any, change of ion drift velocity occurs in the expanded plasma propagation path. It was found the ion drift velocity was increased when magnetic field increased (from 0 up to 200mT). The average ion velocity (cathode material is Ti) increases by factor of 2-3 up to about (3-4) × 10 4 m s −1 with magnetic field strength 200mT applied. Rotation of cathode spot as a result of an applied magnetic field is demonstrated by using Langmuir probes inserted inside the source channel azimuthally. Ion current distribution outside the thruster channel was measured using a set of special assemble of concentric circles plan probe alone the plasma propagation path. It is shown that plasma generated at the cathode spot is guided along the magnetic field line.

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Micro-Vacuum Arc Thruster with Extended Lifetime

Cited by 18 publications

References 3 publications

Microcathode Thruster $(\mu\hbox{CT})$ Plume Characterization

Microcathode Thruster $(\mu\hbox{CT})$ Plume Characterization

Influence of Cathode Shape on Vacuum Arc Thruster Performance and Operation

Performance characterization of the micro-Cathode Arc Thruster and propulsion system for space applications

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