Dielectric Materials with Deposited Electrode Layers for Electrospray Arrays

Kimber, Angela M.; Jorns, Benjamin; Sodano, Henry A.

doi:10.2514/6.2018-4653

Cited by 5 publications

(2 citation statements)

References 22 publications

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“…where r c is the radius of curvature at the tip of the ionic liquid, γ is the surface tension (61.27 mN m −1 at 292.96 K for EMI-DCA), 29) ε 0 is the permittivity of free space, and d is the distance between the tip of the ionic liquid and the extractor, which was a flat plate (d = 1000 nm). [30][31][32] The radius of curvature was assumed to be equal to the inner radius of the capillary emitter. 33) The values of the experimental data were smaller than the theoretical values, likely because the radius of curvature was overestimated and the extractor was not entirely flat.…”

Section: Ion Emission Experimentsmentioning

confidence: 99%

Fabrication of nano-capillary emitter arrays for ionic liquid electrospray thrusters

Suzuki

Nagao

Liu

et al. 2021

Jpn. J. Appl. Phys.

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In this study, we fabricated nano-capillary emitter arrays for stable ion emission of ionic liquid electrospray thrusters, employing the fabrication of field emitter arrays or gated nano electron sources. A nano-capillary emitter was successfully fabricated with a 100–300 nm capillary diameter, which prevented ionic liquid leakage by significantly increasing the fluidic impedance of the ionic liquid compared to a previously proposed emitter. An ion emission experiment was conducted with 1-ethyl-3-methylimidazolium dicyanamide as the propellant. Ion emission started at a low voltage of 61 V owing to a small gap of approximately 1 μm between the emitter and extractor electrode. The maximum current density was 43 mA cm−2 on the positive side and −13 mA cm−2 on the negative side without leakage of the ionic liquid, which was more than 100 times higher than that of conventional electrospray thrusters. Moreover, we obtained continuous ion emission without current intercepted by the extractor.

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Section: Ion Emission Experimentsmentioning

confidence: 99%

Fabrication of nano-capillary emitter arrays for ionic liquid electrospray thrusters

Suzuki

Nagao

Liu

et al. 2021

Jpn. J. Appl. Phys.

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“…Ionic liquid thrusters possess several advantages, such as high specific impulse, high efficiency, precise thrust control, low power consumption, and compact size [1,2], that make them suitable for both micro and nano satellite propulsion [3]. Currently, ionic liquid thrusters have been successfully applied in the in-orbit flight of the LISA Pathfinder, validating their capability for drag-free flight [4].…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of the polarity-switching process with different bipolar ionic liquid thruster operating frequencies

WU 吴,

YANG 杨,

LUO 罗

et al. 2024

Plasma Sci. Technol.

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The bipolar ionic liquid thruster employ ionic liquid as propellant to discharge positively and negatively charged high-energy particles under an alternating current(AC) power source, effectively suppressing electrochemical reaction and ensuring charge neutrality. Determining an optimal AC supply power source frequency is critical for sustained stable thruster operation. This study focuses on the emission characteristics of the ionic liquid thruster under varied AC conditions. The AC power supply was set within the frequency range of 0.5 to 64 Hz, with eight specific frequency conditions selected experimentation. The experimental results indicate that the thruster operate steadily within a voltage range of ±1470 to ±1920 V, with corresponding positive polarity current ranging from 0.41 to 4.91 μA and negative polarity current ranging from -0.49 to -4.10 μA. During voltage polarity switching, an emission delay occurs, manifested as a prominent peak signal caused by circuit capacitance characteristics and a minor peak signal resulting from liquid droplets. Extended emission test were conducted at 16 Hz demonstrating approximately 1 hour and 50 minutes of consistent emission before intermittent discharge. These findings underscore the favorable impact of alternating current conditions within the 8 to 16 Hz range on the self-neutralization capability of the ionic liquid thruster.

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