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Study and Simulations of Spacecraft/Plasma Interaction Phenomena and Their Effects on Low Energy Plasma Measurements Stanislas Guillemant

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Study and Simulations of Spacecraft/Plasma Interaction Phenomena and Their Effects on Low Energy Plasma Measurements Stanislas Guillemant Study and Simulations of Spacecraft/Plasma Interaction Phenomena and their Effects on Low Energy Plasma Measurements Stanislas Guillemant To cite this version: Stanislas Guillemant. Study and Simulations of Spacecraft/Plasma Interaction Phenomena and their Effects on Low Energy Plasma Measurements. Earth and Planetary Astrophysics [astro-ph.EP]. Uni- versité Paul Sabatier - Toulouse III, 2014. English. tel-00976017 HAL Id: tel-00976017 https://tel.archives-ouvertes.fr/tel-00976017 Submitted on 9 Apr 2014 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. THTHESEESE`` En vue de l’obtention du DOCTORAT DE L’UNIVERSITE´ DE TOULOUSE D´elivr´e par : l’Universit´eToulouse 3 Paul Sabatier (UT3 Paul Sabatier) Pr´esent´ee et soutenue le 13/02/2014 par : Stanislas GUILLEMANT Etude et Simulations des Ph´enom`enesd’Interactions Satellite/Plasma et de leurs Impacts sur les Mesures de Plasmas Basses Energies´ JURY Franc¸ois FORME Professeur d’Universit´e Pr´esident du Jury Dominique DELCOURT Directeur de Recherche Rapporteur Vincent GENOT´ Astronome Adjoint Directeur des travaux Alain HILGERS Directeur de Recherche Examinateur Bertrand LEMBEGE` Professeur d’Universit´e Examinateur Philippe LOUARN Directeur de Recherche Directeur de th`ese Richard MARCHAND Professeur d’Universit´e Rapporteur Jean-Charles Ing´enieur de Recherche Directeur des travaux MATEO-V´ ELEZ´ Ecole´ doctorale et sp´ecialit´e : SDU2E : Astrophysique, Sciences de l’Espace, Plan´etologie Unit´e de Recherche : Institut de Recherche en Astrophysique et Plan´etologie (UMR 5277) Directeur(s) de Th`ese : Philippe LOUARN , Vincent GENOT´ et Jean-Charles MATEO-V´ ELEZ´ Rapporteurs : Richard MARCHAND et Dominique DELCOURT ii Résumé : Les satellites scientifiques en vol sont immergés dans divers environnements spatiaux, entourés par différents types de plasmas qu’ils sont supposés analyser, en utilisant les instruments ap- propriés de types détecteurs de particules. La simple présence de cette structure dans le plasma conduit à une variété connue d’interactions satellites/plasma qui sont complexes, inter-corrélées, et difficilement considérées dans leur ensemble. L’environnement spatial influence la structure du satellite (courants, charge électrostatique, radiations, etc) qui, en retour, affecte son envi- ronnement proche (émission de particules, attraction / répulsion du plasma ambiant, etc). Fi- nalement les instruments scientifiques embarqués sur les satellites mesurent un environnement local perturbé et il peut être difficile de distinguer le signal naturel des mesures biaisées. Le but de cette thèse et d’étudier et d’améliorer la compréhension des interactions satel- lite/plasma, au moyen de simulations numériques multi-échelles effectuées avec le logiciel Space- craft Plasma Interaction System (SPIS). Notre attention est portée sur le domaine des basses énergies (en dessous de la centaine d’électronvolts) puisque ce sont ces particules qui sont les plus affectées par les perturbations locales. Le but final est d’établir une méthodologie de con- figuration et de simulation des différentes problématiques liées aux satellites immergés dans des environnements spatiaux, permettant une analyse correcte des mesures plasma en identifiant l’environnement naturel non perturbé parmi les données d’instruments polluées et biaisées. Pour atteindre cet objectif nous effectuons en premier lieu une étude paramétrique des interac- tions ayant lieu entre la sonde Solar Probe Plus et le plasma ambiant dans un environnement proche du soleil. Nous présentons les phénomènes ainsi générés tels que les gaines de plasma constituant des barrières de potentiel pour toutes les particules émises par le satellite et le po- tentiel électrostatique négatif de la sonde résultant, et expliquons leurs origines. Le deuxième axe est l’extension de notre modèle Solar Probe Plus à des distances héliocen- triques plus éloignées, permettant l’étude de la formation des gaines de plasma et des barrières de potentiel entre 0,044 UA du soleil et l’orbite terrestre. Cette étude permet de conclure qu’au périhélie de sa mission, à 0,28 UA du soleil, la mission Solar Orbiter sera concernée par des barrières de potentiel locales et de fortes perturbations au niveau de son instrument Electron Analyser System (EAS). Troisièmement, nous procédons à une étude paramétrique d’un détecteur de particules soumis à diverses perturbations, et comparons les résultats avec les mesures théoriques attendues. Cette méthode fournit une première quantification des différentes problématiques perturbatrices de mesures (comme les potentiels non nuls et les particules parasites). Pour finir nous présentons des simulations avancées de notre modèle Solar Orbiter et de son instrument EAS dans divers environnements, ainsi que les quantifications des biais produits par les interactions Solar Orbiter / plasma sur les mesures simulées d’électrons. Un autre cas concernant le satellite Cluster et son détecteur d’électrons embarqué est également détaillé, avec la comparaison des mesures simulées à des données réelles en vol. Le bon accord des deux jeux de données confirme la validité de notre méthode de simulation des interactions satellite/plasma. Mots clés: Plasma du vent solaire, Structures électrostatiques, Charges de satellites, In- struments plasma, Simulations numériques Abstract: In-flight scientific spacecraft are immersed in various space environments, surrounded by dif- ferent types of plasma they are meant to analyse, using dedicated instruments such as parti- cle detectors. The simple presence of a structure in a plasma leads to various known space- craft/plasma interactions which are complex, inter-correlated, and difficult to consider globally. The space environment influences the satellite structure (currents, electrostatic charging, radi- ations, etc) which in turn affects its near environment (particle emission, attraction / repulsion of the ambient plasma, etc). Finally the spacecraft scientific instruments measure a disturbed local environment and it might be difficult to distinguish the natural signal from the biased data. The objective of this thesis is to study and improve the understanding of the spacecraft/plasma interactions, through multi-scale numerical simulations performed with the Spacecraft Plasma Interaction System (SPIS) software. The focus is on the low energy domain (below a hundred of electron-volts) as those particles are the most affected by local disturbances. The final aim is to establish a methodology of configuring and simulating the various issues related to satellites immersed in space environments, allowing to analyse properly plasma measurements by identi- fying the natural undisturbed environment from biased and polluted instrument outputs. To achieve this goal we first perform a parametric study of the Solar Probe Plus/plasma inter- actions in a near-Sun environment. We present the generated phenomena which are the plasma sheaths representing potential barriers for all spacecraft emitted particles and the associated negative equilibrium potential of the probe, and explain their formation. The second axis is the extension of our Solar Probe Plus model to farther heliocentric distances, allowing the study of the plasma sheaths and potential barriers formation between 0.044 AU from the Sun to the Earth orbit. This allows to state that the Solar Orbiter mission at its perihelion (0.28 AU) will be affected by local potential barriers and strong disturbances in the vicinity of its electron instrument: the Electron Analyser System (EAS). Third, we proceed to a parametric simulation study of a particle detector subjected to various disturbing phenomena, and compare the measurements with the analytical outputs, expected when considering only the electrostatic potential of the instrument. This method provides a first quantification of the different data polluting issues (such as non null potentials and parasite particles). Finally advanced simulations of our Solar Orbiter model and its on-board instrument EAS in various environments are presented, with quantifications of the simulated electron measure- ments biases due to the Solar Orbiter/plasma interactions. Another case considered is the Cluster spacecraft and its on-board electron detector is also detailed, with a comparison of simulated measurements to real in-flight data. The good agreement between the two datasets confirm the validity of our methodology of simulating multi-scale satellite/plasma interactions. Keywords: Solar wind plasma, Electrostatic structures, Spacecraft charging, Plasma instru- ments, Numerical simulations iv Acknowledgments I wish to thank first my co-financers: the Centre National d’Etudes Spatiales (CNES) and the Région Midi-Pyrénées, for putting their trust in me. I also thank my two host laboratories. The Institut de Recherche en Astrophysique et Planétologie (IRAP), directed by Martin Giard, where I worked in the department Géophysique Planétaire et Plasmas Spatiaux (GPPS - directed by Michael Toplis). As for the Toulouse centre of the Office National d’Etudes et de Recherches Aéronautiques
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