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Parker Solar Probe FIELDS Instrument Charging in the Near Sun Environment: Part 1: Computational Model
The Spacecraft Interaction Plasma Software package (SPIS), a three dimension particle in cell (PIC) code, was used to model the Parker Solar Probe (PSP) spacecraft and FIELDS instrument and their interactions with the Solar wind. Our SPIS modeling relied on material properties of new spacecraft materials that we had obtained in previous work. The model was used to find the floating potentials of the spacecraft and FIELDS antennas at different distances from the Sun (from 1AU to 0.046AU). We find the following results: At gre ...
Diaz-Aguado, M.~F.; Bonnell, J.~W.; Bale, S.~D.; Wang, J.; Gruntman, M.;
Published by: Journal of Geophysical Research (Space Physics) Published on: may
YEAR: 2021   DOI: 10.1029/2020JA028688
Parker Solar Probe FIELDS Instrument Charging in the Near Sun Environment: Part 2: Comparison of In Flight Data and Modeling Results
This research shows Part II of the Spacecraft Interaction Plasma Software (SPIS) used to model the parker solar probe (PSP) FIELDS instrument and its interactions with the Solar Wind. Flight data were used to run the PSP model and compared with models using past predicted parameters. The effect of voltage biasing between the antenna, its shield, and the spacecraft on the current balance of each surface was investigated at first perihelion (0.16AU). The model data were reduced to I-V curves to find current saturations (analys ...
Diaz-Aguado, M.; Bonnell, J.; Bale, S.; Wang, J.; Gruntman, M.;
Published by: Journal of Geophysical Research (Space Physics) Published on: 05/2021
YEAR: 2021   DOI: 10.1029/2020JA028689
Spacecraft charging and ion wake formation in the near-Sun environment
A three-dimensional, self-consistent code is employed to solve for the static potential structure surrounding a spacecraft in a high photoelectron environment. The numerical solutions show that, under certain conditions, a spacecraft can take on a negative potential in spite of strong photoelectron currents. The negative potential is due to an electrostatic barrier near the surface of the spacecraft that can reflect a large fraction of the photoelectron flux back to the spacecraft. This electrostatic barrier forms if (1) ...
Ergun, R.; Malaspina, D.; Bale, S.; McFadden, J.; Larson, D.; Mozer, F.; Meyer-Vernet, N.; Maksimovic, M.; Kellogg, P.; Wygant, J.;
Published by: Physics of Plasmas Published on: 07/2010
YEAR: 2010   DOI: 10.1063/1.3457484
52.25.-b; 52.30.-q; 94.05.Jq; parker solar probe; plasma density; plasma flow; Solar Probe Plus; space vehicles; spacecraft charging; Spacecraft sheaths wakes and charging; static electrification