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Found 60 entries in the Bibliography.
Showing entries from 51 through 60
| 2014 |
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Integrated Science Investigation of the Sun (ISIS): Design of the Energetic Particle Investigation The Integrated Science Investigation of the Sun (ISIS) is a complete science investigation on the Solar Probe Plus (SPP) mission, which flies to within nine solar radii of the Sun\textquoterights surface. ISIS comprises a two-instrument suite to measure energetic particles over a very broad energy range, as well as coordinated management, science operations, data processing, and scientific analysis. Together, ISIS observations allow us to explore the mechanisms of energetic particles dynamics, including their: (1)\ O ... McComas, D.; Alexander, N.; Angold, N.; Bale, S.; Beebe, C.; Birdwell, B.; Boyle, M.; Burgum, J.; Burnham, J.; Christian, E.; Cook, W.; Cooper, S.; Cummings, A.; Davis, A.; Desai, M.; Dickinson, J.; Dirks, G.; Do, D.; Fox, N.; Giacalone, J.; Gold, R.; Gurnee, R.; Hayes, J.; Hill, M.; Kasper, J.; Kecman, B.; Klemic, J.; Krimigis, S.; Labrador, A.; Layman, R.; Leske, R.; Livi, S.; Matthaeus, W.; McNutt, R.; Mewaldt, R.; Mitchell, D.; Nelson, K.; Parker, C.; Rankin, J.; Roelof, E.; Schwadron, N.; Seifert, H.; Shuman, S.; Stokes, M.; Stone, E.; Vandegriff, J.; Velli, M.; von Rosenvinge, T.; Weidner, S.; Wiedenbeck, M.; Wilson, P.; Published by: Space Science Reviews Published on: 07/2014 YEAR: 2014 DOI: 10.1007/s11214-014-0059-1 CMEs; Corona; ISIS; Parker Data Used; Particle acceleration; SEPs; Solar energetic particles; Solar Probe Plus |
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Five spacecraft-plasma models are used to simulate the interaction of a simplified geometry Solar Probe Plus (SPP) satellite with the space environment under representative solar wind conditions near perihelion. By considering similarities and differences between results obtained with different numerical approaches under well defined conditions, the consistency and validity of our models can be assessed. The impact on model predictions of physical effects of importance in the SPP mission is also considered by comparing re ... Marchand, R.; Miyake, Y.; Usui, H.; Deca, J.; Lapenta, G.; elez, J.; Ergun, R.; Sturner, A.; enot, V.; Hilgers, A.; Markidis, S.; Published by: Physics of Plasmas Published on: 06/2014 YEAR: 2014 DOI: 10.1063/1.4882439 |
| 2013 |
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In this paper, the electrostatic sheath of a simplified spacecraft is investigated for heliocentric distances varying from 0.044 to 1 AU, using the 3-D Particle in Cell software Satellite-Plasma Interaction System. The baseline context is the prediction of sheath effects on solar wind measurements for various missions, including the Solar Probe Plus mission (perihelion at 0.044 AU from the sun) and Solar Orbiter (SO) (perihelion at 0.28 AU). The electrostatic sheath and the spacecraft potential could interfere with the low-e ... Guillemant, Stanislas; Genot, Vincent; Velez, Jean-Charles; Sarrailh, Pierre; Hilgers, Alain; Louarn, Philippe; Published by: IEEE TRANSACTIONS ON PLASMA SCIENCE Published on: 12/2013 YEAR: 2013 DOI: 10.1109/TPS.2013.2246193 |
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This paper describes the implementation of a solar simulator, know as the Solar Environment Simulator (SES), that can simulate solar flux levels up to those encountered at 9.8 solar radii. The paper outlines the design, and the challenges of realizing the SES. It also describes its initial uses for proving out the design of the Solar Winds Electrons, Alphas, and Protons (SWEAP) Faraday cup. The upcoming Solar Probe Plus (SPP) mission requires that its in-situ plasma instrument (the Faraday Cup) survive and operate over an un ... Cheimets, Peter; Bookbinder, Jay; Freeman, Mark; Gates, Richard; Gauron, Thomas; Guth, Giora; Kasper, Justin; McCracken, Kenneth; Podgorski, William; Published by: Proceedings of SPIE - The International Society for Optical Engineering Published on: Arc lamps; Power control; Probes; Test facilities; Parker Engineering |
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This paper describes the implementation of a solar simulator, know as the Solar Environment Simulator (SES), that can simulate solar flux levels up to those encountered at 9.8 solar radii. The paper outlines the design, and the challenges of realizing the SES. It also describes its initial uses for proving out the design of the Solar Winds Electrons, Alphas, and Protons (SWEAP) Faraday cup. The upcoming Solar Probe Plus (SPP) mission requires that its in-situ plasma instrument (the Faraday Cup) survive and operate over an un ... Cheimets, Peter; Bookbinder, Jay; Freeman, Mark; Gates, Richard; Gauron, Thomas; Guth, Giora; Kasper, Justin; McCracken, Kenneth; Podgorski, William; Published by: Published on: YEAR: 2013 DOI: 10.1117/12.2024051 |
| 2012 |
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Solar wind plasma interaction with solar probe plus spacecraft 3-D PIC (Particle In Cell) simulations of spacecraft-plasma interactions in the solar wind context of the Solar Probe Plus mission are presented. The SPIS software is used to simulate a simplified probe in the near-Sun environment (at a distance of 0.044 AU or 9.5 RS from the Sun surface). We begin this study with a cross comparison of SPIS with another PIC code, aiming at providing the static potential structure surrounding a spacecraft in a high photoelectron environment. This paper presents then a s ... Guillemant, S.; enot, V.; elez, J.-C.; Ergun, R.; Louarn, P.; Published by: Annales Geophysicae Published on: 07/2012 YEAR: 2012 DOI: 10.5194/angeo-30-1075-2012 |
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Solar wind plasma interaction with solar probe plus spacecraft 3-D PIC (Particle In Cell) simulations of spacecraft-plasma interactions in the solar wind context of the Solar Probe Plus mission are presented. The SPIS software is used to simulate a simplified probe in the near-Sun environment (at a distance of 0.044 AU or 9.5 RS from the Sun surface). We begin this study with a cross comparison of SPIS with another PIC code, aiming at providing the static potential structure surrounding a spacecraft in a high photoelectron environment. This paper presents then a s ... Guillemant, S.; enot, V.; elez, J.-C.; Ergun, R.; Louarn, P.; Published by: Annales Geophysicae Published on: 07/2012 YEAR: 2012 DOI: 10.5194/angeo-30-1075-2012 |
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Active solar array thermal control system for the solar probe plus spacecraft The Solar Probe Plus (SPP) spacecraft will orbit the Sun closer than any other previous probe. As dictated by the current mission design, the spacecraft will achieve many perihelia as close as 9.5 RS from the Sun. During those passes, it will encounter a solar flux of ~500 suns, or 70 W/cm2. This flux is more than 50 times larger than the solar heating seen by any previous spacecraft. During the entire mission, the spacecraft and science instruments will be protected by a Thermal Protection System (TPS), and elect ... Ercol, Carl; Guyette, Greg; Cho, Wei-Lin; Published by: 42nd International Conference on Environmental Systems 2012, ICES 2012 Published on: Cooling; Cooling systems; Flight control systems; Probes; Solar cell arrays; Spacecraft; Thermoelectric equipment; Waste heat; Parker Engineering |
| 2010 |
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Solar Probe Plus: Mission design challenges and trades NASA plans to launch the first mission to the Sun, named Solar Probe Plus, as early as 2015, after a comprehensive feasibility study that significantly changed the original Solar Probe mission concept. The original Solar Probe mission concept, based on a Jupiter gravity assist trajectory, was no longer feasible under the new guidelines given to the mission. A complete redesign of the mission was required, which called for developing alternative trajectories that excluded a flyby of Jupiter. Without the very powerful gravi ... Published by: Acta Astronautica Published on: 11/2010 YEAR: 2010 DOI: 10.1016/j.actaastro.2010.06.007 |
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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 |
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