Flexible variable-specific-impulse electric propulsion systems for planetary missions

Chesta, E.; Estublier, Denis; Fallis, Benjamin; Gengembre, E.; Amo, J. Gonzalez del; Kutufa, N.; Nicolini, D.; Saccoccia, G.; Casalino, Lorenzo; Dumazert, P.; Prioul, M.; Boeuf, Jean-Pierre; Bouchoule, A.; Wallace, Neil; Noci, G.; Berti, M.; Saverdi, M.; Biagioni, L.; Marcuccio, Salvo; Cadiou, Anne; Darnon, Franck; Jolivet, Laurent

doi:10.1016/j.actaastro.2005.07.053

Cited by 14 publications

(7 citation statements)

References 4 publications

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“…The combination of gravity assists with low thrust is extremely effective, as the initial DV budget of 16 km s À1 could be reduced to $4.5 km s À1 , albeit with a significant increase in cruise time (from 2.6 to 6.4 years). Additional information on SEP optimization methods can be obtained from Chesta et al (2006), while the navigation aspects of BepiColombo are addressed by Yarnoz et al (2006) and Alessi et al (2012).…”

Section: Ion Propulsionmentioning

confidence: 98%

Mission Analysis Issues for Planetary Exploration Missions

Langevin

2015

Treatise on Geophysics

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Section: Ion Propulsionmentioning

confidence: 98%

Mission Analysis Issues for Planetary Exploration Missions

Langevin

2015

Treatise on Geophysics

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“…3 are deduced from a hybrid simulation. [8][9][10] In this model, the description of ion transport is kinetic while the description of electron is fluid. Ionization is however deduced from a Monte Carlo simulation of electron transport.…”

Section: -3mentioning

confidence: 99%

“…In the experiments reported in the literature, the intermediate electrode was not emissive. The paper by Chesta et al 9 indicates that "the possibility to include an emitting internal electrode (hollow cathode) in the ionization stage has been carefully assessed and finally rejected". The authors did not explain this choice which is not consistent with ideal DSHT operation and model predictions.…”

Section: -3mentioning

confidence: 99%

ID-HALL, a new double stage Hall thruster design. I. Principle and hybrid model of ID-HALL

et al. 2018

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In Hall thrusters, ions are extracted from a quasineutral plasma by the electric field induced by the local drop of electron conductivity associated with the presence of a magnetic barrier. Since the electric field is used both to extract and accelerate ions and to generate the plasma, thrust and specific impulse are not independent in a Hall thruster. There is a need for versatile thrusters that can be used for a variety of maneuvers, i.e., that can operate either at high thrust or at high specific impulse for a given power. The double stage Hall thruster (DSHT) design could allow a separate control of ionization and acceleration, and hence separate control of thrust and specific impulse. In the DSHT configuration, a supplementary plasma source (ionization stage), independent of the applied voltage, is added and placed upstream of the magnetic barrier (acceleration stage). The DSHT concept is also well adapted to the use of alternative propellants, lighter and with a less efficient ionization than xenon. Several designs of double stage Hall thrusters have been proposed in the past, but these attempts were not really successful. In this paper, we present a brief review of the main DSHT designs described in the literature, we discuss the relevance of the DSHT concept, and, on the basis of simple physics arguments and simulation results, we propose a new design, called ID-HALL (Inductive Double stage HALL thruster). In this design, the ionization stage is a magnetized inductively coupled RF plasma. The inductive coil is inside the central cylinder of the thruster and located nearby the acceleration stage. Preliminary modeling results of this DSHT are described.

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“…Additional information on SEP optimization methods can be obtained from Chesta et al (2006), while the navigation aspects of BepiColombo are addressed by Yarnoz et al (2006). The combination of gravity-assists with low thrust is extremely effective, as the inital ÁV budget of 16 km s À1 could be reduced to $4.15 km s À1 , albeit with a significant increase in cruise time (from 2.5 to 6 years).…”

Section: Ion Propulsionmentioning

confidence: 99%

Mission Analysis Issues for Planetary Exploration Missions

Langevin

2007

Treatise on Geophysics

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Flexible variable-specific-impulse electric propulsion systems for planetary missions

Cited by 14 publications

References 4 publications

Mission Analysis Issues for Planetary Exploration Missions

Mission Analysis Issues for Planetary Exploration Missions

ID-HALL, a new double stage Hall thruster design. I. Principle and hybrid model of ID-HALL

Mission Analysis Issues for Planetary Exploration Missions

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