Investigation of the laboratory model of a thruster with anode layer operating with air and nitrogen-oxygen mixture

Духопельников, Д. В.; Riazanov, V. A.; Shilov, S. O.; Manegin, D. S.; Sokolov, R. A.

doi:10.1063/5.0036251

Cited by 3 publications

(2 citation statements)

References 6 publications

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“…The system is theoretically applicable to any planetary body with an atmosphere, and can drastically reduce the on-board propellant storage requirement, while extending the mission's lifetime [2]. Many ABEP concepts have been investigated in the past based on radio frequency ion thrusters (RIT) [3][4][5][6][7][8][9][10][11][12], ECR-based thruster [13][14][15][16][17], Hall-effect thrusters (HET) [18][19][20][21][22][23][24][25], and plasma thrusters [26]. The only laboratory tested ABEP systems to date are the ABIE developed in Japan, composed of an annular intake and an ECR-based thruster into one device [13][14][15][16], and the RAM-HET system developed in Europe, comprised of the intake and a HET assembled into one device [20][21][22][23][24].…”

Section: Abep Conceptmentioning

confidence: 99%

Design of an intake and a thruster for an atmosphere-breathing electric propulsion system

Romano

Herdrich²,

Chan³

et al. 2022

CEAS Space J

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Challenging space missions include those at very low altitudes, where the atmosphere is the source of aerodynamic drag on the spacecraft, that finally defines the mission's lifetime, unless a way to compensate for it is provided. This environment is named Very Low Earth Orbit (VLEO) and it is defined for h < 450 km. In addition to the spacecraft's aerodynamic design, to extend the lifetime of such missions, an efficient propulsion system is required.One solution is Atmosphere-Breathing Electric Propulsion (ABEP), in which the propulsion system collects the atmospheric particles to be used as propellant for an electric thruster. The system could remove the requirement of carrying propellant on-board, and could also be applied to any planetary body with atmosphere, enabling new missions at low altitude ranges for longer missions' duration. One of the objectives of the H2020 DISCOVERER project, is the development of an intake and an electrode-less plasma thruster for an ABEP system.This article describes the characteristics of intake design and the respective final designs based on simulations, providing collection efficiencies up to 94%. Furthermore, the radio frequency (RF) Helicon-based plasma thruster (IPT) is hereby presented as well, while its performances are being evaluated, the

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Section: Abep Conceptmentioning

confidence: 99%

Design of an intake and a thruster for an atmosphere-breathing electric propulsion system

Romano

Herdrich²,

Chan³

et al. 2022

CEAS Space J

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“…The optimal design and operation regime for TAL-type Hall thrusters with xenon and alternative propellants have been investigated [4,5]. Hamada et al developed a 5-kW TAL characterized by a magnetic field geometry where the peak of the magnetic flux density is located downstream of the channel exit [6].…”

Section: Introductionmentioning

confidence: 99%

Wall Ion Loss Reduction by Acceleration Zone Shifting in Anode-Layer Hall Thruster

Kawashima¹,

Hamada²,

Kawabata³

et al. 2022

Preprint

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A review of air-breathing electric propulsion: from mission studies to technology verification

2022

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Air-breathing electric propulsion (ABEP) allows for lowering the altitude of spacecraft operations below 250 km, in the so-called Very Low Earth Orbits (VLEOs). Operations in VLEOs will give radical advantages in terms of orbit accessibility, payload performance, protection from radiations, and end-of-life disposal. ABEP combines an intake to collect the residual atmosphere in front of the spacecraft and an electric thruster to ionize and accelerate the atmospheric particles. Such residual gas can be exploited as a renewable resource not only to keep the spacecraft on a VLEO, but also to remove the main limiting factor of spacecraft lifetime, i.e., the amount of stored propellant. Several realizations of the ABEP concept have been proposed, but the few end-to-end experimental campaigns highlighted the need to improve the concept functional design and the representativeness of simulated atmospheric flows. The difficulty in recreating the VLEO environment in a laboratory limits the data available to validate scaling laws and modelling efforts. This paper presents a comprehensive review of the main research and development efforts on the ABEP technology.

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Investigation of the laboratory model of a thruster with anode layer operating with air and nitrogen-oxygen mixture

Cited by 3 publications

References 6 publications

Design of an intake and a thruster for an atmosphere-breathing electric propulsion system

Design of an intake and a thruster for an atmosphere-breathing electric propulsion system

Wall Ion Loss Reduction by Acceleration Zone Shifting in Anode-Layer Hall Thruster

A review of air-breathing electric propulsion: from mission studies to technology verification

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