Field-emitter arrays for vacuum microelectronics

Spindt, C.A.; Holland, C.E.; Rosengreen, A.; Brodie, I.

doi:10.1109/16.88525

Cited by 354 publications

(147 citation statements)

References 25 publications

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“…Field emission cathodes are used as neutralizers for space propulsion devices and as electron sources for flat-panel displays, focused electron beams for electron microscopy, and neutralization for spacecraft mass spectrometry [6][7][8][9]. The motivation for the research reported here is the limited lifetime of many current microfabricated field emitters, with the exception of carbon nanotube cathodes, which have demonstrated impressive life tests [10].…”

mentioning

confidence: 99%

Regenerable Field Emission Cathode for Spacecraft Neutralization

Makela

Washeleski

King

2009

Journal of Propulsion and Power

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This research investigates the discharge characteristics of a field emission cathode for use in electric propulsion that has the ability to be regenerated when the emitter tip becomes damaged. Emitter tip regeneration is achieved by taking advantage of Taylor cone formation from an operating liquid-metal ion source. Tip formation is accomplished by solidifying, or quenching, the ion-emitting cone to preserve the sharp protrusion so that it can then be used for electron emission. Electron emission I-V curves were taken after tips were formed by quenching the liquid-metal ion source at ion discharge currents ranging from 1 to 25 A. Fowler-Nordheim modeling was then used to estimate the emitter tip radii of each quenched liquid-metal ion source. Results of the Fowler-Nordheim modeling were promising, showing the ability to regenerate tips and to control the features of the resulting tips by varying the ion current during the quench process. The set of experiments that are reported demonstrated the regeneration process of emitter tip radii ranging from approximately 30-45 nm from a tip quenched at 2 A down to tip radii of 15-22 nm when quenched at 25 A.

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confidence: 99%

Regenerable Field Emission Cathode for Spacecraft Neutralization

Makela

Washeleski

King

2009

Journal of Propulsion and Power

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“…An array of vertical field emitters forms a large-area flat electron source. 4,5 Unfortunately, the vertical structure may be undesirable for circuit implementation due to the difficulties in achieving geometrical dimensions such as gap spacing to be identical over all devices on the substrate. In contrast, the geometry of the planar structure ( Fig.…”

mentioning

confidence: 99%

Vacuum nanoelectronics: Back to the future?—Gate insulated nanoscale vacuum channel transistor

Han¹,

Oh²,

Meyyappan³

2012

Applied Physics Letters

211

143

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Growth of large-size-two-dimensional crystalline pentacene grains for high performance organic thin film transistors AIP Advances 2, 022138 (2012) Effects of substrate strain and electrical stress on lattice dynamics, defects, and traps in strainedSi/Si0.81Ge0.19n-type metal-oxide-semiconductor field effect transistors J. Appl. Phys. 111, 104507 (2012) Threshold voltage shift and drain current degradation by negative bias temperature instability in Si (110) pchannel metal-oxide-semiconductor field-effect transistor Appl. Phys. Lett. 100, 212109 (2012) High-speed metal-insulator transition in vanadium dioxide films induced by an electrical pulsed voltage over nano-gap electrodes Appl. Phys. Lett. 100, 213507 (2012) Kubo-Greenwood approach for the calculation of mobility in gate-all-around nanowire metal-oxide-semiconductor field-effect transistors including screened remote Coulomb scattering-Comparison with experiment

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“…6 This device will be designed to emit up to 1 A of electron current. Electron emission is achieved by applying a gate voltage of approximately 75-100 V between an array of millions of microscopic needle points and a gate electrode.…”

Section: Electron Emittermentioning

confidence: 99%

The Terminator Tether - Autonomous deorbit of LEO spacecraft for space debris mitigation

Hoyt

Forward

2000

38th Aerospace Sciences Meeting and Exhibit

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The Terminator Tether ª is a lightweight, low-cost device that will use electrodynamic drag generated by a conducting tether to remove satellites and upper stages from low Earth orbit when they have completed their missions. In order to investigate and optimize t h e performance of the device, we developed a detailed numerical simulation that includes models for tether dynamics, electrodynamic interactions with the EarthÕs ionosphere, Spindt cathode electron emission, and other relevant physics. Using this simulation, we examined t h e electrical behavior of the tether-plasma circuit, and found that a device with a tether length of 5-10 km can utilize some of the power generated by the tether to drive its own circuitry without severely affecting the deorbit rate. Thus the device can be independent of the host spacecraftÕs power systems during deorbit. Because an uncontrolled electrodynamic tether is dynamically unstable, we developed a feedback-control scheme and verified its operation using simulations. Using the same models and control scheme, we investigated the performance of t h e device for disposing of spacecraft from various orbital inclinations and altitudes. We found that a tether device massing 2% of the host spacecraft mass can deorbit an upper stage from a 50¡, 400 km orbit in under two weeks, a mid-LEO satellite from a 50¡, 850 km orbit in under three months, or a high-LEO satellite from a 50¡, 1400 km orbit in less than a year.

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Field-emitter arrays for vacuum microelectronics

Cited by 354 publications

References 25 publications

Regenerable Field Emission Cathode for Spacecraft Neutralization

Regenerable Field Emission Cathode for Spacecraft Neutralization

Vacuum nanoelectronics: Back to the future?—Gate insulated nanoscale vacuum channel transistor

The Terminator Tether - Autonomous deorbit of LEO spacecraft for space debris mitigation

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