On the influence that the ground electrode diameter has in the propulsion efficiency of an asymmetric capacitor in nitrogen gas

Martins, Alexandre A.; Pinheiro, Mario J.

doi:10.1063/1.3562874

Cited by 22 publications

(18 citation statements)

References 12 publications

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“…ρμE is known as the drift current and ρu the convective current. A common modelling assumption is to neglect the neutral fluid velocity relative to the ion drift velocity, μE [12][13][14]. Ionic wind velocities at the laboratory scale have been reported to be between 1 and 10 m s −1 [25].…”

Section: Theorymentioning

confidence: 99%

“…This has also motivated literature focused on developing computational models to solve the EHD governing equations [12][13][14][15][16][17]. In aerospace engineering, research efforts have focused on using dielectric barrier discharges (DBDs) to provide aerodynamic flow control to prevent subsonic boundary layer separation over aerofoils [18][19][20].…”

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confidence: 99%

“…Both studies modelled a configuration similar to that of the 'lifter' concept, with Martins & Pinheiro [13] concluding that the thrust is electrostatic in origin and is concentrated on the collecting electrode. Another numerical analysis by Martins & Pinheiro [14] quantified the sensitivity of thrust output with respect to collecting electrode diameter, determining that thrust increased with diameter owing to higher levels of ionization at the emitting electrode. A further numerical analysis performed by Martins [15] considered an improved thruster design with multiple collecting stages for a single emitting electrode.…”

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confidence: 99%

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Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Gilmore

Barrett

2015

Proc. R. Soc. A.

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ResearchCite this article: Gilmore CK, Barrett SRH. 2015 Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion. Proc. R. Soc Previous work has characterized electrohydrodynamic (EHD) thruster performance, determining that thrust-to-power ratios are comparable with that of conventional propulsion at the laboratory scale. Achievable thrust density of EHD propulsion has yet to be experimentally quantified and could be a limiting factor in its application. In this paper, we quantify the achievable thrust density for a wire-to-cylinder electrode geometry using positive corona discharges for electrode pairs operating in parallel and in series. Geometric parameters, including the non-dimensional inter-pair and stage spacings, are varied, and the effect on current and thrust is measured. We estimate a maximum thrust per unit area of 3.3 N m −2 and a maximum thrust per unit volume of 15 N m −3 , which we compare with the characteristic thrust density of a range of aircraft. We find that trade-offs exist between thrust density and the achieved thrust-to-power ratio, where increases in the former through either increased power input or pair packing density lead to decreases in the latter. We conclude that EHD propulsion has the potential to be viable from both an energy efficiency perspective (our previous study) and a thrust density perspective (this paper), with the greatest likelihood of viability for smaller aircraft such as unmanned aerial vehicles.

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Section: Theorymentioning

confidence: 99%

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confidence: 99%

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confidence: 99%

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Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Gilmore

Barrett

2015

Proc. R. Soc. A.

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“…Among them the most accepted are the ones that consider the produced ions (through the corona effect) being accelerated by the electrical field configuration and causing, after a sequence of collisions, the transference of linear momentum to the surrounding neutral air molecules [2][3][4][5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Lifter - High voltage plasma levitation device

Cattani

Vannucci²,

Souza³

2015

Rev. Bras. Ensino Fís.

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This paper shows in detail the construction and operation of an apparatus that levitates when submitted to voltages greater or of the order of 20 kV. This device, which basically corresponds to an asymmetric capacitor, is commonly known in the literature by the name 'lifter '. It also will be shown in this article, through rather simplified calculations, that the physics grounds of the observed levitation effect are intrinsically related to the transference of linear momentum of the ions (positive or negative) to the surrounding atmosphere. These ions are produced within the conductor of very small curvature (hence, great electrical potential) due to the so called corona effect and, once created, they are immediately accelerated by the intrinsic electric field lines configuration, producing multiple collisions with the air molecules, causing the transference of momentum and, therefore, provoking the observed lifter ascendant impulsion. Keywords: air ionization, corona effect, ion propulsion, asymmetrical capacitor, ion craft, lifter.Este artigo descreve em detalhe a construção e operação de um sistema mecânico que levita quando submetido a tensões maiores ou iguais a 20 kV. Este dispositivo, que corresponde basicamente a um capacitor assimétrico, e conhecido na literatura pelo nome de 'lifter '. Tambémé mostrado neste trabalho, através de cálculos razoavelmente simplificados, que o mecanismo físico responsável pelo efeito de levitação está intrinsecamente relacionado com a transferência de momento linear deíons (positivos ou negativos) para o ar circundante. Estesíons são produzidos ao redor do condutor de menor curvatura (portanto com maior potencial elétrico) devido ao chamado efeito corona e, uma vez criados, eles são imediatamente acelerados pela configuração do campo elétrico existente, produzindo múltiplas colisões com as moléculas de ar, causando a transferência de momento e, consequentemente, provocando no lifter um movimento ascendente. Palavras-chave: ionização do ar, efeito corona, propulsão iônica, capacitor assimétrico, nave iônica, lifter.

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“…[1][2][3][4][5][6][7][8] This device can propel a vehicle without any on-board propellants in planetary atmosphere. EHD thruster is also called "CDPA (Corona Discharge Plasma Actuator)" 13) .…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Fundamental Characteristics of Electro-Hydrodynamic Thruster for Mobility in Planetary Atmosphere

Shibata

Watanabe

Yano

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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The EHD (electro-hydrodynamic) thruster seems suitable for a device of mobility at planetary exploration because of its propellant-less nature. In this paper, the fundamental characteristics of the EHD thruster are investigated from a viewpoint of the applicability to the planetary exploration. The numerical analysis of the drift-diffusion equations shows that it works irrespective to the polarity of the electrodes because the polarity of the produced ions is also changed. This fact implies that it will work in different atmospheric composition with different polarity of the produced ions. It is also numerically found that the thrust tends to increase with the decrease in the ambient pressure. For simplicity of discussion, a simple analytical model to describe the energy conversion efficiency is derived, and it indicates that higher efficiency is expected in higher Knudsen number regime. Both the above results suggest that the EHD thruster is promising especially in planetary atmosphere with low density.

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On the influence that the ground electrode diameter has in the propulsion efficiency of an asymmetric capacitor in nitrogen gas

Cited by 22 publications

References 12 publications

Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Lifter - High voltage plasma levitation device

Numerical Study on Fundamental Characteristics of Electro-Hydrodynamic Thruster for Mobility in Planetary Atmosphere

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