Hybrid Particle-in-Cell Simulations of Magnetic Sail in Laboratory Experiment

Kajimura, Yoshihiro; Usui, Hideyuki; Funaki, Ikkoh; Ueno, Kazuyuki; Nunami, M.; Shinohara, I.; Nakamura, Masao; Yamakawa, Hiroshi

doi:10.2514/1.45096

Cited by 27 publications

(13 citation statements)

References 15 publications

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“…Our result shows the drag coefficient is 2.9 (note that the drag coefficient in Fig. 6 is converted using the definition of C D by Fujita [11] and Kajimura et al [16]); our result is in good agreement with the results from the kinetic simulations (C D 3:2 0:4).…”

Section: Resultssupporting

confidence: 88%

“…Fujita [11] and Kajimura et al [16] conducted three-dimensional kinetic simulations for wide range of the plasma interaction scale (from the ion kinetic scale to the MHD scale) for the case of 90 deg, and the drag coefficient in the MHD scale was reported as 3.6 by Fujita [11] and 3.0 by Kajimura et al [16]. Our result shows the drag coefficient is 2.9 (note that the drag coefficient in Fig.…”

Section: Resultsmentioning

confidence: 48%

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Analysis of Thrust Characteristics of a Magnetic Sail in a Magnetized Solar Wind

Nishida

Funaki

2012

Journal of Propulsion and Power

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The magnetic sail is an advanced space propulsion concept that uses an artificial magnetosphere for capturing the solar wind energy. In this study, the interaction of the solar wind with the magnetosphere of a magnetic sail has been simulated based on the resistive magnetohydrodynamics model in two-dimensional space and the plasmadynamic characteristics of magnetic sail were evaluated. When the solar wind is not magnetized by the interplanetary magnetic field, the attitude of the magnetic sail spacecraft is static stable when the magnetic moment vector is perpendicular to the solar wind flow direction. The interplanetary magnetic field not only enhances a drag force in the direction leaving the sun (i.e., thrust) but also acts on the pitching moment; the pitching moment due to the interplanetary magnetic field rotates the magnetic sail spacecraft so as to align the magnetic moment vector parallel to the interplanetary magnetic field. Despite the weak interplanetary magnetic field adopted in the simulation, which is 1 order of magnitude lower than the typical value, the pitching moment coefficient is significant. The attitude stability of the magnetic sail is hence strongly affected by the interplanetary magnetic field. Nomenclaturecurrent density vector M = acoustic Mach number, magnetic moment m p = mass of proton p = pressure q sw = solar wind dynamic pressure R c = radius of a magnetic sail R m = magnetic Reynolds number S c = characteristic area of the flowfield T p = pitching moment v = velocity vector x, y = coordinate variable = angle of attack = tilt angle of interplanetary magnetic field = angle between interplanetary magnetic field and magnetic moment vector = specific heat ratio = resistivity 0 = magnetic permeability in vacuum = density Subscript c = characteristic value

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Section: Resultssupporting

confidence: 88%

Section: Resultsmentioning

confidence: 48%

Analysis of Thrust Characteristics of a Magnetic Sail in a Magnetized Solar Wind

Nishida

Funaki

2012

Journal of Propulsion and Power

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“…Another approach to obtaining the electric and magnetic fields is to directly solve Faraday's law and Ampere's law in Maxwell's equations [9]. The model is called the EM model, and it was used in the full particle and particle-fluid hybrid modeling of magnetic sails [8,10]. It was reported that the ESMS model yields almost the same thrust as the EM model in the full particle simulations of a 2D magnetic sail, for which the condition number is 600 [11].…”

Section: Iib Em Fieldmentioning

confidence: 99%

Particle Simulation of Plasma Drag Force Generation in the Magnetic Plasma Deorbit

Kawashima¹,

Bak²,

Matsuzawa³

et al. 2018

Journal of Spacecraft and Rockets

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The magnetic plasma deorbit method has been proposed for micro and nanosatellites in the low earth orbit (LEO). The magnetic plasma deorbit utilizes the plasma drag force generated by the interaction between space plasma and the magnetic field surrounding magnetic torquers (MTQs). In this study, the plasma drag force generated by the magnetic plasma deorbit method is estimated by using a plasma flow simulation based on the fully kinetic model. The dependences of the plasma drag force on the MTQ angle, atmospheric plasma density, and MTQ magnetic moment are investigated. The simulation results show that the structures of the bow shock and magnetosphere are formed in the vicinity of the MTQs. The predicted plasma drag force is 105.2 nN for an MTQ of 10 A m 2 when the MTQ magnetic moment is parallel to the satellite velocity direction. The plasma drag force shows a strong dependence on the magnetic moment angle. In addition, the plasma drag force is proportional to the atmospheric plasma density and the MTQ magnetic moment. Steady drag force generation in the magnetic plasma deorbit is validated, and the sensitivities of the drag force to the relevant parameters are elucidated.

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“…Seeing the detail of Fig.17, however, one can see that laboratory experiment shows rather small thrust level than that by numerial simulation. This discrepancy is caused as a result of the collisional effect that is inevitable in laboratory [Kajimura et al, 2010], and it means that the laboratory experiment cannot predict the entire feature of collisionless plasmas in space.…”

Section: Thrust Measurement Of Magsailmentioning

confidence: 99%