Electric solar wind sail optimal transit in the circular restricted three body problem

Quarta, Alessandro A.; Aliasi, Generoso; Mengali, Giovanni

doi:10.1016/j.actaastro.2015.06.017

Cited by 7 publications

(13 citation statements)

References 18 publications

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“…These flight times are nearly coincident with those obtained in Ref. [7] for an optimal transfer between the two classical Lagrange points L 1 → L 4 (445 days), and L 1 → L 5…”

Section: Reaching Triangular Lagrangian Pointssupporting

confidence: 87%

“…Accordingly, the analysis extends the results discussed in Ref. [7] (where a single value of characteristic acceleration is considered) and provides a parametric study of the E-sail performance for this significant mission scenario. Indeed a mission to the Lagrange's triangular points would allow a nearby analysis (possibly using multiple flybys)…”

supporting

confidence: 64%

“…The approach used in the solution is described in Ref. [7], while the differential equations have been integrated in double precision using a variable order Adams-Bashforth-Moulton solver scheme [14,15] with absolute and relative errors of 10 −12 .…”

Section: Numerical Resolution Of the Problemmentioning

confidence: 99%

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Heliocentric phasing performance of electric sail spacecraft

2016

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“…These flight times are nearly coincident with those obtained in Ref. [7] for an optimal transfer between the two classical Lagrange points L 1 → L 4 (445 days), and L 1 → L 5…”

Section: Reaching Triangular Lagrangian Pointssupporting

confidence: 87%

supporting

confidence: 64%

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Heliocentric phasing performance of electric sail spacecraft

2016

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“…The interest towards mission design using propellantless propulsion systems has significantly promoted the study of the E-sail behaviour in the interplanetary environment [4,5,6,7,8,9]. In a preliminary mission design phase, the E-sail thrust may be estimated with a simplified model in which the tethers are assumed to be coplanar, and the E-sail takes the shape of a rigid disk [10].…”

Section: Introductionmentioning

confidence: 99%

Electric sail static structural analysis with finite element approach

et al. 2020

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“…Finally, note that the transfer phase, from launch to the design AEP, is not considered this analysis. In fact, since an E-sail is capable of providing thrust only when there is no shielding action due to a planetary magnetic field, the velocity increment required to leave the Earth's magnetosphere must be provided by the upper stage of the launch vehicle, while the heliocentric transfer phase has been investigated elsewhere [36] in an optimal framework.…”

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confidence: 99%

Artificial Collinear Lagrangian Point Maintenance With Electric Solar Wind Sail

Niccolai

Caruso

Quarta

et al. 2020

IEEE Trans. Aerosp. Electron. Syst.

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This paper discusses the maintenance of an L1type artificial equilibrium point in the Sun-[Earth+Moon] circular restricted three-body problem by means of an Electric Solar Wind Sail. The reference configuration instability is compensated for with a feedback control law that adjusts the grid voltage as a function of the distance from the natural L1 point. Two different control strategies are analyzed assuming the solar wind fluctuations to be modelled through a statistical approach.Index Terms-Electric Solar Wind Sail, artificial Lagrangian equilibrium point, solar wind fluctuations, circular restricted three-body problem I. IntroductionA N Electric Solar Wind Sail (E-sail) is an innovative propulsion system, invented in 2004 by Pekka Janhunen [1], which generates a propulsive acceleration by exploiting the solar wind dynamic pressure through the electrostatic interaction between a grid of charged tethers and the solar wind ions. After an on-ground experimental campaign [2], [3], the first in-flight testing of E-sail technology is being attempted in a geocentric environment by flying a variant of the E-sail working principle, the plasma brake [4], [5], [6]. The latter is a deorbiting system, consisting of a single charged tether that interacts with ions in the ionosphere to generate a drag. The first test was tried by the Estonian satellite EstCube [7], but a failure to the tether unreel mechanism occurred [8]. Currently, the Finnish Aalto-1 [9] satellite is equipped with a plasma brake tether that should enable an end-of-life deorbiting [10].The major advantage of an E-sail-based spacecraft over more conventional systems is in its capability of providing thrust without consuming any propellant mass [11], [12],[13], [14], in a similar way to a solar sail [15]. The latter however uses the interaction of the solar radiation pressure with a large and highly reflective surface. The peculiarity of propellantless propulsive systems allows exotic mission scenarios to be envisaged, such as the creation and maintenance of an artificial equilibrium point (AEP) in which the relative position of the spacecraft is constant with respect to the Sun and the [Earth+Moon]. Indeed, because an

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Electric solar wind sail optimal transit in the circular restricted three body problem

Cited by 7 publications

References 18 publications

Heliocentric phasing performance of electric sail spacecraft

Heliocentric phasing performance of electric sail spacecraft

Electric sail static structural analysis with finite element approach

Artificial Collinear Lagrangian Point Maintenance With Electric Solar Wind Sail

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