Integrated Studies of Electric Propulsion Engines during Flights in the Earth’s Ionosphere

Marov, M. Ya.; Filatyev, A.S.

doi:10.1134/s0010952518020041

Cited by 15 publications

(4 citation statements)

References 2 publications

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“…N 2, see [39,40] for details) as a propellant and capable of operation in ultra-low Earth orbits. Spacecraft with such a thruster show outstanding performance including 140 km s −1 jet velocity and neutralization losses of 0.3% [41]. Recently, we verified the possibility of operation of an air-breathing thruster in low Earth orbits, taking into account the aerodynamic forces acting on the spacecraft [42].…”

Section: Resultsmentioning

confidence: 75%

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Nano-graphite field-emission cathode for space electric propulsion systems

et al. 2022

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Improving the thruster efficiency is a crucial challenge for the development of space electric propulsion systems, especially advanced air-breathing thrusters utilizing the surrounding rarefied atmosphere as fuel. A significant reduction in thruster power consumption can be achieved by using field emission (FE) cathodes that do not require heating and have the highest energy efficiency. In this work, we study FE from nano-graphite thin films, consisting of carbon nanostructures with a high aspect ratio, and demonstrate their suitability for use in the space electric propulsion systems. The films shown appropriate FE characteristics in a wide range of gas pressures at high current loads in constant and pulsed operation modes. Based on the obtained experimental results, nano-graphite cathodes were employed for the design of an electron gun with increased reliability and minimized energy losses associated with electron extraction. The possibility of using such a gun in a specific air-breathing satellite operating in low Earth orbits is demonstrated.

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Section: Resultsmentioning

confidence: 75%

“…The operation and design of the air-breathing thruster are described in [41]. Briefly, this thruster has a diameter of 100 mm and provides an ion flux with total current of about I 0  ~200 mA.…”

Section: Resultsmentioning

confidence: 99%

Nano-graphite field-emission cathode for space electric propulsion systems

et al. 2022

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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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“…The intake designs developed at IRS [21][22][23] are based on a long slender cylindrical intake with a honeycomb duct section in the front optimized for both Earth and Mars atmosphere that can achieve η c = 0.43. The Central Aerohydrodynamic Institute TsAGI [24][25][26][27][28][29][30] developed a similar concept, but the honeycomb is changed for a squared duct section delivering η c = 0.33 − 0.34. SITAEL and the von Karman Institute for Fluid Dynamics, Aeronautics and Aerospace [13][14][15][16][17]31], refined the intake design that started with the 2007 ESA RAM-EP study [3].…”

Section: Intake Literature Reviewmentioning

confidence: 99%

RF Helicon-based Inductive Plasma Thruster (IPT) Design for an Atmosphere-Breathing Electric Propulsion system (ABEP)

et al. 2020

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Challenging space missions include those at very low altitudes, where the atmosphere is source of aerodynamic drag on the spacecraft. To extend such missions lifetime, an efficient propulsion system is required. One solution is Atmosphere-Breathing Electric Propulsion (ABEP). It collects atmospheric particles to be used as propellant for an electric thruster. The system would minimize the requirement of limited propellant availability and can also be applied to any planet with atmosphere, enabling new mission at low altitude ranges for longer times. Challenging is also the presence of reactive chemical species, such as atomic oxygen in Earth orbit. Such species cause erosion of (not only) propulsion system components, i.e. acceleration grids, electrodes, and discharge channels of conventional EP systems. IRS is developing within the DISCOVERER project, an intake and a thruster for an ABEP system. The paper describes the design and implementation of the RF helicon-based inductive plasma thruster (IPT). This

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Integrated Studies of Electric Propulsion Engines during Flights in the Earth’s Ionosphere

Cited by 15 publications

References 2 publications

Nano-graphite field-emission cathode for space electric propulsion systems

Nano-graphite field-emission cathode for space electric propulsion systems

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

RF Helicon-based Inductive Plasma Thruster (IPT) Design for an Atmosphere-Breathing Electric Propulsion system (ABEP)

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