Electro-rocket ramjet thruster for compensating the aerodynamic drag of a low-orbit spacecraft

Kanev, S. V.; Petukhov, V. G.; Попов, Г. А.; Khartov, S. A.

doi:10.3103/s106879981503006x

Cited by 11 publications

(4 citation statements)

References 2 publications

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“…A new aspect in EJE usage has recently appeared: the compensation of spacecraft deceleration in the upper atmosphere [7]. For this purpose, the most promising solution is the use of outboard air as the working body [7][8][9].…”

Section: Introductionmentioning

confidence: 99%

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Effective sputtering yields of titanium, titanium nitride, and molybdenum induced by nitrogen ions and ions of nitrogen-oxygen mixtures

Духопельников

Riazanov

Vorob’ev

et al. 2016

J. Synch. Investig.

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This work is dedicated to studying the effects of nitrogen ions and ions of nitrogen and oxygen mixtures on the surface of titanium, titanium nitride, and molybdenum. The usage of magnetron sputtering systems as a model device to study the effect of reactive gases on elements of electric jet engines is proposed and justified. The processes of sputtering of a surface exposed to non-monoenergetic ion beams are studied. The effective sputtering yields of titanium, titanium nitride, and molybdenum induced by argon and nitrogen ions and ions of nitrogen-oxygen mixtures at various intermediate-energy ion beams are determined. It is shown that the sputtering yields of reactive-gas ions are significantly lower than the sputtering yields of inert gases.

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Section: Introductionmentioning

confidence: 99%

“…For this purpose, the most promising solution is the use of outboard air as the working body [7][8][9]. The use of a mixture of reactive gases as the EJE working body requires a more detailed understanding of the processes occurring under the action of a nitrogen and oxygen ion flux on an EJE's structural elements.…”

Section: Introductionmentioning

confidence: 99%

Effective sputtering yields of titanium, titanium nitride, and molybdenum induced by nitrogen ions and ions of nitrogen-oxygen mixtures

Духопельников

Riazanov

Vorob’ev

et al. 2016

J. Synch. Investig.

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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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Electro-rocket ramjet thruster for compensating the aerodynamic drag of a low-orbit spacecraft

Cited by 11 publications

References 2 publications

Effective sputtering yields of titanium, titanium nitride, and molybdenum induced by nitrogen ions and ions of nitrogen-oxygen mixtures

Effective sputtering yields of titanium, titanium nitride, and molybdenum induced by nitrogen ions and ions of nitrogen-oxygen mixtures

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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