Microfabricated emitter array for an ionic liquid electrospray thruster

Nakagawa, K.; Tsuchiya, Toshiyuki; Takao, Yoshinori

doi:10.7567/jjap.56.06gn18

Cited by 25 publications

(31 citation statements)

References 36 publications

(46 reference statements)

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“…We find that the LM is always smaller than the transversal one, and that both are proportional to |B| 2 at low fields (as expected from symmetry considerations [42]), while at higher fields the |B| dependence follows a lower slope. The magnitude of the magnetoresistance is quite similar to what found experimentally in p-type Si and Ge (the only exception is the TM of p-type Ge which is about one order of magnitude larger than in diamond) [43]. The results are in overall good agreement with the experimental data, and the differences between theory and experiment might be related to the unclear doping content of the measured samples and the fact that the experimental data have been taken with respect to different orientations of J e and B.…”

supporting

confidence: 82%

Magnetotransport phenomena in p -doped diamond from first principles

Macheda

Bonini

2018

Phys. Rev. B

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We present a first-principles study of the magneto-transport phenomena in p-doped diamond via the exact solution of the linearized Boltzmann transport equation, in which the materials' parameters, including electron-phonon and phonon-phonon interactions, are obtained from density functional theory. This approach gives results in very good agreement with experimental data for Hall and drift mobilities, low-and high-field magnetoresistance and Seebeck coefficient, including the phonon drag effect, in a range of temperatures and carrier concentrations. In particular, our results provide a detailed characterisation of the exceptionally high values for mobility and Seebeck coefficient, and predict a large magnetic-field driven enhancement of the Seebeck coefficient, of up to 30% in a magnetic field of 40 kOe already at room temperature.

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supporting

confidence: 82%

Magnetotransport phenomena in p -doped diamond from first principles

Macheda

Bonini

2018

Phys. Rev. B

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“…84 Externally wetted microfabricated emitter tips have recently been reported. 85 However, the vast majority of MEMS emitters uses capillary type emitters as described above, called internally wetted emitters in this context. The hydraulic resistance of the capillaries has been identified as a key parameter for stable operation.…”

Section: -13mentioning

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

256

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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“…The calculation model has the same sizes and conditions as experiments by the authors. 7) The emitter cone has a shape of a pencil which is 0.07 mm in radius and 0.2 mm in height. An area surrounded by dotted lines is considered in this study.…”

Section: Configurationmentioning

confidence: 99%

“…It was assumed that the ions were extracted from the emitter tip when the threshold voltage of +1.7 kV or more was applied to the emitter chip, which was an averaged value measured in previous experiments. 7) Figure 5 shows a static potential distribution by the voltage applied to the emitter chip in the case of no ions in the calculation area. Here and all the other distributions are mirrored with respect to the z-axis.…”

Section: Slew Ratementioning

confidence: 99%

“…1) Electrospray thrusters have been already fabricated and operated in space, and many studies of electrospray thrusters were reported so far. [2][3][4][5][6][7] However, the number of operations is still small, and optimization of electrospray thrusters is in progress. Here, the authors simulated ion beams extracted from an emitter tip using Particle-in-Cell simulations, which are often conducted in conventional plasma thrusters.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Investigation of Steady and Transient Ion Beam Extraction Mechanisms for Electrospray Thrusters

Emoto

Tsuchiya

Takao

2018

AEROSPACE TECHNOLOGY JAPAN

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Electrospray thrusters are simple propulsion systems, which can be operated on nanosatellites, and it is possible to reduce components of high pressure gas systems using ionic liquid as a propellant. However, evaluations of electrospray thrusters are difficult in experiments since the size of emitter cones is on the order of micrometers. Then, the authors performed Particle-in-Cell simulations of ions in the electrospray thruster and investigated ion beam extraction mechanisms in steady and transient flows numerically. The simulation results show that steady ion beam distributions were rarely affected by ion species. On the other hand, it was clarified that a jet affected the ion beam profiles. In addition, the authors evaluated propulsion performance of the electrospray thruster, which showed a thrust of about 64 nN per emitter and a specific impulse of about 6400 s. In the transient flow, the ion beam behavior showed rapid responses when applied voltages with or without a slew rate are assumed.

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Microfabricated emitter array for an ionic liquid electrospray thruster

Cited by 25 publications

References 36 publications

Magnetotransport phenomena in p -doped diamond from first principles

Magnetotransport phenomena in p -doped diamond from first principles

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

Numerical Investigation of Steady and Transient Ion Beam Extraction Mechanisms for Electrospray Thrusters

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