Full 3D PIC simulation of Hall Effect Thrusters

Passaro, A.; Nania, F.; Vicini, A.

doi:10.2514/6.2006-3246

Cited by 2 publications

(3 citation statements)

References 7 publications

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“…The model of [22] was then improved and a more accurate description of the plasma sheath was included, allowing for a direct assessment of the wall erosion [24,25]. Similarly, SITAEL developed the PICPlus code to simulate the plume of Hall thrusters [26]. Results of hybrid-PIC numerical investigations can be found, for example, in [2,[25][26][27].…”

Section: Model Descriptionmentioning

confidence: 99%

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Influence of the magnetic field configuration on the plasma flow in Hall thrusters

Andreussi¹,

Giannetti²,

Leporini³

et al. 2017

Plasma Phys. Control. Fusion

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In Hall propulsion, the thrust is provided by the acceleration of ions in a plasma generated in a cross-field configuration. Standard thruster configurations have annular channels with an almost radial magnetic field at the channel exit. A potential difference is imposed in the axial direction and the intensity of the magnetic field is calibrated in order to hinder the electron motion, while leaving the ions non-magnetised. Magnetic field lines can be assumed, as a first approximation, as lines of constant electron temperature and of thermalized potential. In typical thruster configurations, the discharge occurs inside a ceramic channel and, due to plasma-wall interactions, the electron temperature is typically low, less than few tens of eV. Hence, the magnetic field lines can be effectively used to tailor the distribution of the electrostatic potential. However, the erosion of the ceramic walls caused by the ion bombardment represents the main limiting factor of the thruster lifetime and new thruster configurations are currently under development. For these configurations, classical first order models of the plasma dynamics fail to grasp the influence of the magnetic topology on the plasma flow. In the present paper, a novel approach to investigate the correlation between magnetic field topology and thruster performance is presented. Due to the anisotropy induced by the magnetic field, the gradients of the plasma properties are assumed to be mainly in the direction orthogonal to the local magnetic field, thus enabling a quasi-one-dimensional description in magnetic coordinates. Theoretical and experimental investigations performed on a 5 kW class Hall thruster with different magnetic field configurations are then presented and discussed.

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Section: Model Descriptionmentioning

confidence: 99%

“…Similarly, SITAEL developed the PICPlus code to simulate the plume of Hall thrusters [26]. Results of hybrid-PIC numerical investigations can be found, for example, in [2,[25][26][27].…”

Section: Model Descriptionmentioning

confidence: 99%

Influence of the magnetic field configuration on the plasma flow in Hall thrusters

Andreussi¹,

Giannetti²,

Leporini³

et al. 2017

Plasma Phys. Control. Fusion

View full text Add to dashboard Cite

show abstract

“…The PICPluS code family is composed of two-and threedimensional hybrid/full particle in cell (PIC) codes, developed at Alta since 2002 ( [1][2][3][4][5][6][7][8]). The codes allow one to perform timeaccurate plasma plume/spacecraft interaction simulations in four different ways: 1) full particle simulation on a multiblock grid composed of Cartesian structured boxes with external solid surfaces, 2) full particle simulation on a nonstructured grid including surfaces and solid bodies ( Fig.…”

Section: The Picplus Code Familymentioning

confidence: 99%

Numerical Rebuilding of SMART-1 Hall Effect Thruster Plasma Plume

Passaro

Vicini

Nania

et al. 2010

Journal of Propulsion and Power

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The SMART-1 flight data provided an excellent opportunity for extending validation of plume prediction codes to actual flight conditions. This paper will present the results obtained for the numerical simulation of the SMART-1 plasma plume using the PICPluS particle in cell code, which had been previously validated using ground experiment data. This activity can be considered as the first important step in the direction of a full in-flight validation for the code models and algorithms. A description of the implemented physical models is provided, followed by simulation results of experimental data from Alta's tests and from the literature. Finally, the results of the code application to the SMART-1 mission are presented, focusing on the simulation of retarding potential analyzer measurement, spacecraft floating potential, and interaction of the plasma field with the satellite (in particular the solar array). The results show that, although the possibility of dangerous interaction between the electric propulsion system and the spacecraft is very limited, a number of complex phenomena arise due to the use of the electric propulsion system in orbit. For example, the interaction between the plume and the solar array orientation leads to complex patterns for the spacecraft floating potential. Eventually, full three-dimensional simulation is therefore needed to accurately model this kind of phenomena with a realistic description of the involved geometries. Nomenclature e = electron charge, C k = Boltzman constant, J=K I = current, A n = number density, m 3 P = probability, -r = position vector, m T = temperature, K Vd = discharge potential, V ", "0 = dielectric constant, F=m = charge density, C=m 3 , ' = electric scalar potential, V

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Full 3D PIC simulation of Hall Effect Thrusters

Cited by 2 publications

References 7 publications

Influence of the magnetic field configuration on the plasma flow in Hall thrusters

Influence of the magnetic field configuration on the plasma flow in Hall thrusters

Numerical Rebuilding of SMART-1 Hall Effect Thruster Plasma Plume

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