As a result of the last 60 years of satellite launches, a significant amount of space debris has been generated in Earth orbit. Growing consensus amongst experts over the last decade, has suggested that removing existing debris, alongside mitigation efforts, can assist in controlling the size of the low Earth orbit (LEO) population. However, no objective or long-term strategy exist to ensure the most effective use of active debris removal (ADR). The way we utilise near-Earth space, and the way the space environment will behave in the future will directly affect the number of debris objects required to be removed. This then, makes it difficult to identify any potential future ADR strategy that will perform effectively in all possible future cases. This thesis explores a novel adaptive strategy that determines how many debris objects should be removed to control the size of the LEO debris population. The strategy adapts and adjusts the number of removals performed by ADR in response to the evolution of the debris population. The framework for the strategy was inspired by the methods incorporated in adaptive management and control engineering. The University of Southampton’s Debris Analysis and Monitoring Architecture to the Geosynchronous Environment (DAMAGE) model was used to represent the space environment, whilst a new debris model entitled the Computational Adaptive Strategy to Control Accurately the Debris Environment (CASCADE) was used to predict the evolution of DAMAGE, and required removal rate. Predictions using DAMAGE were run under a variety of launch, explosion, mitigation and solar activity for both the ≥10 cm and ≥5 cm LEO populations. Two key parameters of the adaptive strategy were also investigated: modifying the frequency of implementation and exploring different high-level objeives for the strategy. Using the adaptive strategy increased the probability of achieving its objective and required fewer removals, as each prediction had a bespoke number of removals. On average, 3.1 removals (standard deviation: 1.2) were required to provide an 88% probability in preventing the growth of the ≥10 cm LEO population. Whereas, implementing realistic variations in launch, explosion, mitigation and solar activity, on average, 6.3 removals (standard deviation: 6.8) were required to prevent the growth of the ≥5 cm LEO population with 76% confidence. This compared with a “traditional” strategy of removing five objects per year that only provided 49% confidence. This approach then, represents a rational method to calculate the number of removals required to ensure the future sustainability of outer space activities.

A new type of space debris was recently discovered by Schildknecht in near -geosynchronous orbit (GEO). These objects were later identified as exhibiting properties associated with High Area-to-Mass ratio (HAMR) objects. According to their brightness magnitudes (light curve), high rotation rates and composition properties (albedo, amount of specular and diffuse reflection, colour, etc), it is thought that these objects are multilayer insulation (MLI). Observations have shown that this debris type is very sensitive to environmental disturbances, particularly solar radiation pressure, due to the fact that their shapes are easily deformed leading to changes in the Area-to-Mass ratio (AMR) over time. This thesis proposes a simple effective flexible model of the thin, deformable membrane with two different methods. Firstly, this debris is modelled with Finite Element Analysis (FEA) by using Bernoulli-Euler theory called “Bernoulli model”. The Bernoulli model is constructed with beam elements consisting 2 nodes and each node has six degrees of freedom (DoF). The mass of membrane is distributed in beam elements. Secondly, the debris based on multibody dynamics theory call “Multibody model” is modelled as a series of lump masses, connected through flexible joints, representing the flexibility of the membrane itself. The mass of the membrane, albeit low, is taken into account with lump masses in the joints. The dynamic equations for the masses, including the constraints defined by the connecting rigid rod, are derived using fundamental Newtonian mechanics. The physical properties of both flexible models required by the models (membrane density, reflectivity, composition, etc.), are assumed to be those of multilayer insulation. Both flexible membrane models are then propagated together with classical orbital and attitude equations of motion near GEO region to predict the orbital evolution under the perturbations of solar radiation pressure, Earth’s gravity field, luni-solar gravitational fields and self-shadowing effect. These results are then compared to two rigid body models (cannonball and flat rigid plate). In this investigation, when comparing with a rigid model, the evolutions of orbital elements of the flexible models indicate the difference of inclination and secular eccentricity evolutions, rapid irregular attitude motion and unstable cross-section area due to a deformation over time. Then, the Monte Carlo simulations by varying initial attitude dynamics and deformed angle are investigated and compared with rigid models over 100 days. As the results of the simulations, the different initial conditions provide unique orbital motions, which is significantly different in term of orbital motions of both rigid models. Furthermore, this thesis presents a methodology to determine the material dynamic properties of thin membranes and validates the deformation of the multibody model with real MLI materials. Experiments are performed in a high vacuum chamber (10-4 mbar) replicating space environment. A thin membrane is hinged at one end but free at the other. The free motion experiment, the first experiment, is a free vibration test to determine the damping coefficient and natural frequency of the thin membrane. In this test, the membrane is allowed to fall freely in the chamber with the motion tracked and captured through high velocity video frames. A Kalman filter technique is implemented in the tracking algorithm to reduce noise and increase the tracking accuracy of the oscillating motion. The forced motion experiment, the last test, is performed to determine the deformation characteristics of the object. A high power spotlight (500-2000W) is used to illuminate the MLI and the displacements are measured by means of a high resolution laser sensor. Finite Element Analysis (FEA) and multibody dynamics of the experimental setups are used for the validation of the flexible model by comparing with the experimental results of displacements and natural frequencies.

Les ceintures de radiation provoquent des dégâts irréversibles sur les satellites les traversant, détériorant ainsi les instruments de mesure embarqués. Les étudier est utile au développement de matériaux adaptés et résistants. Depuis les années 90, l'ONERA-DESP étudie les ceintures de radiations des planètes magnétisées, telle que la Terre ou Jupiter, grâce au modèle Salammbô. Salammbô prend en compte les processus physiques de l'environnement radiatif pour recréer les populations d'électrons peuplant les ceintures. Dans cette étude, il s'agit de développer un modèle des ceintures de radiations internes de Saturne, basé sur les travaux précédents. Avant les années 2000, Pioneer 11 et Voyager 2 ne permettaient pas un développement suffisamment avancé d'un modèle de ceintures de radiations de Saturne. La mission Cassini apporte ensuite quantités d'observations et de données pour mener une étude plus approfondie de ces ceintures. Cette thèse débute par l'analyse de la magnétosphère interne de Saturne : anneaux, satellites, nuages de neutres...L'interaction des particules des ceintures de radiations avec ces différents paramètres se traduit par le calcul de coefficients de diffusion. Ces coefficients sont intégrés à l'équation de transport et permettent de comprendre les mécanismes perturbant la distribution des électrons au sein des ceintures de radiations. Les résultats obtenus sont comparés aux mesures faites par les sondes Pioneer 11, Voyager 2 et Cassini. / Radiation belts cause irreversible damages to on-board instrument materials. Studies about radiation belts can be useful for development of materials that will stand such environment. Since the 1990's, ONERA develops models of radiation belts of magnetized planets, such as the Earth or Jupiter. These previous work lead to a physical model, named Salammbô. Salammbô is based on physical processes that dominate the planetary magnetosphere in order to recreate electron populations of radiation belts. ONERA is now able to develop an electron radiation belt model for Saturn's environment, i.e., a new version of Salammbô. Before the 2000's, Pioneer 11 and Voyager 2 did not allow a good development of a Salammbô model in the case of Saturn. Nowadays, the Cassini mission gives a lot of information about Saturn, its magnetosphere and its environment to start a study about radiation belts of Saturn. This thesis begins with the analyse of the kronian magnetosphere : rings, satellites, neutral clouds, etc. Interaction between radiation belt particle and these different parameters lead to diffusion coefficients. Diffusion coefficients are integrated into the Salammbô code and imply a better comprehension of mechanisms that can interfere with the electron distribution of radiation belts. Results have been compared with observations of Pioneer 11, Voyager 2 and Cassini spacecrafts.

Miniaturized satellites are one of the fastest growing sectors in the space industry, allowing cheap access to space. These satellites are currently limited by their lack of orbit control and their lifetime is therefore determined by the natural, drag-induced, de-orbiting. These issues can be solved using a dedicated propulsion system. Cold-gas micro-thrusters, successfully flown on miniaturized satellites, are characterised by a very low specific impulse (typically less than 100 s), which considerably limits their capabilities. Moreover, they require pressurized tanks, pressure regulators and valves that may significantly increase the dry mass of the system. Pulsed Plasma Thrusters (PPTs) represent an excellent alternative to the chemical thrusters thanks to their high scalability in terms of geometry, power input and performance. Within this research programme, the factors that affect the lifetime of solid state propellant PPTs for miniaturized satellites (e.g. Cubesat and nanosatellites) applications have been studied and addressed. Moreover, efforts have been made to optimise a PPT as a sub-system to be integrated into a satellite spacecraft. This included the characterization of the electromagnetic noise that PPTs generate and that may cause failures on the other Cubesat subsystems and a study aimed at the optimization of the PPT ignition process to produce a lighter and more reliable conditioning electronics. To complete all these tasks, a miniaturized PPT (called PPTCUP, which stands for PPT for Cubesat Propulsion) has been developed and tested in collaboration with Mars Space Ltd and Clyde Space Ltd. Results from the PPTCUP test campaign have proved the reliability of the thruster, being able to perform a number of shots almost two times bigger than the nominal number required to demonstrate the discharge chamber lifetime. Moreover, it has been found that the unit can work correctly in the range of the Cubesat operating temperatures, withstands the mechanical vibrations during launch and has main natural frequencies compliant with the Cubesat requirements. The results of the EMC characterization test show that the electromagnetic noise generated during the main PPT discharge is mostly compliant with the requirements or small enough to be impossible to distinguish from the facility background noise. The dedicated study to identify the best spark plug system working with a relative low breakdown voltage has shown that the semiconductor- coated spark plug insulator are able to trigger the PPT main discharge at a lower voltage (i.e. about 1700 V against the 7500 V needed for the no-coated propellant rods) without affecting the overall thruster performances.

Depuis le début de l’ère spatiale avec le lancement du satellite Spoutnik 1 en 1957, les ceintures de radiationterrestres n’ont cessé de faire l’objet d’études du fait de leur dangerosité pour les satellites mais aussi pour l’êtrehumain. En effet, lors d’une forte activité solaire, l’injection de particules dans cet environnement radiatif peut induiredes flux jusqu’à 1000 fois plus élevés que par temps calme. Par conséquent, il est important d’en comprendrela physique ainsi que la dynamique au cours de ce que l’on appelle un orage géomagnétique. Dans ce but, le Département Physique Instrumentation Environnement et Espace (DPhIEE) de l’ONERA développe depuis maintenantplus de 20 ans la famille de modèles Salammbô reproduisant de façon robuste et en trois dimensions la dynamiquedes particules piégées dans ces ceintures. Néanmoins, bien que précis au-delà d’environ 100 keV, la physique et leshypothèses prises en compte dans ce modèle restent insuffisantes en deçà. En effet, aux basses énergies, les ceintures de radiation ne peuvent plus être considérées comme homogènes autour de la Terre. L’objectif de cette thèse a donc été de prendre en compte une quatrième dimension, le temps magnétique local (MLT), afin de mieux reproduire l’évolution des structures fines lors d’un orage géomagnétique. La première partie s’est portée sur l’optimisation du schéma numérique. L’ajout d’une quatrième dimension induit, via l’apparition d’un terme d’advection, une forte diffusion numérique qu’il convient de limiter, tout en tenant compte du temps de calcul. L’équation statistique implémentée a alors été discrétisée selon un schéma de type Beam-Warming du second ordre couplé à un limiteur Superbee, garantissant une propagation satisfaisante de la distribution initiale. Une fois les problèmes numériquesmaitrisés, les différents mécanismes physiques pilotant la dynamique des particules piégées ont été implémentésdans le code, avec une attention toute particulière sur la dépendance en MLT de l’interaction onde-particule. Laprise en compte des champs électriques magnétosphériques fut également nécessaire. En effet, ils constituent l’undes moteurs principaux du mouvement des particules de basses énergies. Le modèle Salammbô 4D a ensuite étévalidé par comparaison avec le modèle 3D déjà existant sur une simulation de l’orage magnétique de Mars 2015.Les résultats ont montré une bonne restitution de la dynamique des ceintures de radiation, avec en plus l’accès à laphase principale de l’orage. Cet évènement a ensuite été modélisé à plus basse énergie pour constater la dynamiqueasymétrique des électrons piégés avec le rôle prépondérant du champ électrique de convection. La comparaison avecles données du satellite THEMIS a montré une bonne modélisation des différents processus physiques, notammentcelui de « dropout » par traversée de la magnétopause. Enfin, la mise en place d’une condition limite dynamiquemodulée par les paramètres du vent solaire et dépendante du MLT ouvre de nombreuses perspectives. / Since the beginning of the Space Era with the launch of Spoutnik 1 spacecraft in 1957, the radiation belts havebeen studied by scientists due to their hazardousness on both spacecrafts and humans. Indeed, particles are injectedduring strong solar activity and can induce fluxes thousand times higher than quiet time ones. Thus, it’s veryimportant to understand the nature of physics-based processes and the consecutive dynamic during a geomagneticstorm. For this purpose, the Department Physics Instrumentation Environment and spacE (DPhIEE) at ONERA hasbeen developing the Salammbô models family for more than 20 years which robustly reproduce in three dimensionsthe dynamics of trapped particles in the radiation belts. Nevertheless, although they are reliable at high energy, thephysics-based processes and the hypothesis taken into account are inadequate at lower energies, below a few hundredsof keV. Indeed, the radiation belts can no longer be considered as homogeneous around the Earth. The aim of thisPhD research work was to take into account a fourth coordinate, the Magnetic Local Time (MLT), in order to betterreproduce the thinnest structures occurring during a geomagnetic storm. The first part of this work focused on theoptimization of the numerical scheme. By the emergence of an advective term, the inclusion of a fourth coordinateinduces a strong numerical diffusion that has to be controlled and limited without deteriorating the computingefficiency. So, the implemented statistical equation was discretized using a Beam-Warming scheme coupled with theSuperbee limiter, which guarantee us an adequate propagation of the initial distribution. Once numerical issues havebeen resolved and controlled, all the different mechanisms driving the dynamics of the trapped particles have beenimplemented into the code, taking into account their MLT dependency, especially for the wave-particle interaction.Taking into account the magnetospheric electric fields was also necessary. Indeed, they correspond to one of themain drivers of the low energy particles motion. Then, the Salammbô 4D model has been validated by a comparisonwith the 3D one on a simulation of the March 2015 geomagnetic storm. The results showed a good restitutionof the dynamics of the radiation belts, refining the storm main phase resolution. Thereafter, this event has beensimulated at lower energy to analyze the asymmetry of the dynamics of trapped electrons highlighting the primerole of the convection electric field. The comparison with data from THEMIS spacecraft showed a good modelingof the different physics-based processes, in particular regarding dropouts as controlled by magnetopause shadowingeffect. Finally, the implementation of a solar wind driven outer boundary condition opens up new prospects.

This research work developed an innovative computational approach to the preliminary design of low-thrust trajectories optimising multiple mission criteria. Low-Thrust (LT) propulsion has become the propulsion system of choice for a number of near Earth and interplanetary missions. Consequently, in the last two decades a good wealth of research has been devoted to the development of computational method to design low-thrust trajectories. Most of the techniques, however, minimise or maximise a single figure of merit under a set of design constraints. Less effort has been devoted to the development of efficient methods for the minimisation (or maximisation) of two or more figures of merit. On the other hand, in the preliminary mission design phase, the decision maker is interested in analysing as many design solutions as possible against different trade-off criteria. Therefore, in this PhD work, an innovative Multi-Objective (MO), memetic optimisation algorithm, called Multi-Agent Collaborative Search (MACS2), has been implemented to tackle low-thrust trajectory design problems with multiple figures of merit. Tests on both academic and real-world problems showed that the proposed MACS2 paradigm performs better than or as well as other state-of-the-art Multi-Objective optimisation algorithms. Concurrently, a set of novel approximated, first-order, analytical formulae has been developed, to obtain a fast but reliable estimation of the main trade-off criteria. These formulae allow for a fast propagation of the orbital motion under a constant perturbing acceleration. These formulae have been shown to allow for the fast and relatively accurate propagation of long LT trajectories under the typical acceleration level delivered by current engine technology. Various applications are presented to demonstrate the validity of the combination of the analytical formulae with MACS2. Among them, the preliminary design of the JAXA low-cost DESTINY mission to L2, a novel approach to the optimisation under uncertainty of deflection actions for Near Earth Objects (NEO), and the de-orbiting of space debris with low-thrust and with a combination of low-thrust and solar radiation pressure.

This thesis is about how space technology is experienced in the social domain and how its purpose is recast from different viewpoints. The author is an artist and the approach taken foregrounds qualities of experience and viewpoint in which artists have a particular investment. This approach opens up the ways that affect, agency and authorship cross social domains that are directly and indirectly associated with the production of space technologies. A key focus is a group project led by the author that was initiated in response to the launch in October 2008 of the Chandrayaan-1 spacecraft by the Indian Space Research Organisation (ISRO). The project took place in Bengaluru, India where the spacecraft was built. Taking the ambivalence that surrounds the uses and purposes of space technologies as a starting point, a description of the spacecraft is developed from a number of viewpoints, including the mission scientists, public media and the participants of the artist-led project. The interventionist strategies of the project shed light on the ways that technologies can be accessed through their imaginaries and this has significance for large-scale technologies, such as spacecraft, for which physical access is delimited and much of the infrastructure is invisible or hidden from public view. The thesis proposes ways of reinstating missed qualities of viewpoint and experience within the affective spaces of space technology through the imperative to articulate first-person engagements with the world that is bound into artistic interpretation. What is further proposed is that by picturing the interrelations and flows of space technology in social domains through the lenses of experience and viewpoint, a 'technographic picture' is created that then becomes available as a tool with which to re-imagine spacefaring. This is a crucial addition to discussions about the interplay between science, technology and society that recognises the intimate spaces at the core of such large-scale concepts. It offers a new transdisciplinary modality that incorporates an artistic approach with which to make sense of the structurally ambivalent pursuits of spacefaring.

Lorsqu’un avion atterrit, la force principale nécessaire pour arrêter l’avion est obtenue par le freinage. Par une réduction de la vitesse de rotation des roues, les freins provoquent une vitesse de glissement entre les pneus et la piste. C’est cette différence de vitesse qui génère la force de freinage capable de stopper l’avion. La modélisation de cette force est essentielle pour l’estimation de la longueur de piste à l’atterrissage. Les modèles classiques utilisés par les avionneurs sont assez simplistes et dérivent expérimentalement des modèles de frictions les plus simples. De sorte que ces modèles sont dans l’incapacité d’estimer l’influence de paramètres clefs influençant la force de freinage. Il s’agit, en particulier de la pression des pneus, de la nature de la gomme, de la température ambiante et de celle de la gomme, de l’état de la piste, de sa texture, etc. L’objectif de la thèse a été de développer un modèle de contact pneu-piste capable d’estimer la force de freinage. C’est le « Brush Model » qui a servi de base à cette modélisation. En phase de freinage la zone de contact est constituée d’une première zone de déformation de la gomme qui crée une force résistante en suivant la loi de Hooke, puis d’une seconde zone de glissement dont la force de résistance suit la loi de Coulomb. Ce modèle a été amélioré grâce aux résultats de la mécanique des structures pour la loi de Hooke et grâce aux résultats de la tribologie pour la loi de Coulomb. Ces deux modélisations faisant appel aux données issues de la science des matériaux. L’ensemble de ces modélisations a été enrichi par une coopération avec plusieurs centres de recherches ayant fourni de nombreux résultats expérimentaux. Le modèle obtenu a ensuite été confronté avec des résultats d’essais en vol obtenus avec « Airbus Operations S.A.S ». La thèse a validé le prétraitement des données d’essais ainsi que le processus d’identification qui a permis de montrer l’accord du modèle avec les résultats expérimentaux obtenus lors des essais en vol. Cette modélisation donne des résultats très encourageants, elle permet une compréhension beaucoup plus approfondie des effets de l’environnement sur les forces de freinage. De sorte que cette thèse a permis d’améliorer très sensiblement la compréhension fondamentale des phénomènes en jeu lors du freinage, au contact entre le pneu et la piste. Chez Airbus, les résultats obtenus vont servir de base pour les travaux à venir sur ce thème. / As an aircraft lands on a runway, the principal force acting to stop the aircraft within the confines of the runway is generated by the brakes. The brakes cause the tire’s rotational speed to slow down with regards to the aircraft’s speed over the ground. This difference in speed causes friction and it is this friction that is the principal force to stop the aircraft. In order to be able to estimate the stopping distance of an aircraft an understanding of this friction is essential. Traditionally, aircraft manufactures have relied on simplistic, empirically derived friction models. However, these empirical models cannot estimate the influence of several key factors that are known (scientifically) to affect friction such as the rubber temperature, the runway texture, the ambient air temperature and the rubber composition to name a few. This PhD work aims to develop a frictional model that can be used to estimate the friction developed between an aircraft tire and the runway. A model commonly known as the Brush Model, is derived for usewith aircraft tires and runways. The underlying physics of this model are developed using the established scientific theories of tribology, material science and strength of materials. Coordination with several research institutes provides experimental results to reinforce the model. The model is then compared with flight test results obtained from a partnership with Airbus OperationsS.A.S. The PhD works demonstrates the entire validation process from flight test data cleaning, the derivation of a curve-fitting algorithm and the matching of derived model with the flight test data. The modeling has shown very encouraging results. It allows for a much deeper understanding of the environmental effects on friction. This PhD work has greatly improved the fundamental understanding of friction and will serve as a base for future works with Airbus.

Les ceintures de radiation correspondent à la région de la magnétosphère dans laquelle se trouvent les particules de hautes énergies. Le couplage entre le vent solaire et la magnétosphère donne lieu à des variations des flux de particules sur plusieurs ordres de grandeurs. L’objectif de cette thèse est d’observer et caractériser ces variations de flux d’électrons au passage de différents types d’événements tels que les régions d’interaction en co-rotation (CIRs) et les éjections de masse coronale interplanétaires (ICMEs). Pour cela, nous avons traité et analysé les données de plusieurs types: paramètres du vent solaire, indices géomagnétiques et flux d’électrons dans les ceintures de radiation. Dans les trois premiers chapitres, nous rendons compte de la complexité de l’environnement spatial Terrestre et présentons les différentes données utilisées. Les travaux de thèse sont ensuite organisés en quatre chapitres. Premièrement, nous utilisons les mesures des satellites NOAA-POES afin de caractériser les flux d’électrons dans les ceintures. Nous étudions ensuite les différences de variations de flux causées par les CIRs et les ICMEs en fonction de l’énergie des électrons et du paramètre L*. Après avoir montré le fort lien entre les intensités d’orages magnétiques et les variations de flux, nous nous focalisons sur les ICMEs et la variabilité des orages qu’elles causent. Enfin, nous insistons sur l’importance des enchaînements d’événements. Après avoir quantifié la forte tendance qu’ont les ICMEs à former des séquences, nous réalisons une étude statistique sur les orages qu’elles causent, puis trois études de cas afin d’illustrer leurs effets sur les ceintures. / The radiation belts are the toroidal region within the inner magnetosphere where high energetic particles are located. The coupling between the solar wind and the magnetosphere leads to strong variations of particle fluxes that can therefore increase or decrease over several orders of magnitude. The aim of this thesis is to observe and characterize the variations of fluxes during the crossing of several types of events originating from the sun such as Corotating Interaction Regions (CIRs) and Interplanetary Coronal Mass Ejections (ICMEs). To do so, we processed and analyzed the data of various types : solar wind parameters, geomagnetic indices, and electron fluxes within the radiation belts. In the three first chapters, we report on the complexity of the Terrestrial space environment and we present the Solar-Terrestrial system and the data used. Then, our work is organized around four chapters. First, we characterized the electron fluxes within the radiation belts as measured by the NOAA-POES spacecrafts. Then, we studied the difference between the variations of fluxes caused by the CIRs and the ICMEs depending on the energy and the L* parameter. After establishing strong links between the intensity of magnetic storms and the variations of fluxes, we focused on the ICMEs and the variability of the related magnetic storms. Eventually, we emphasized the importance of the sequences of events. After quantifying the trend of the ICMEs to form sequences, we performed a statistical study on the magnetic storms caused by such sequences. Finally three study cases were performed in order to illustrate the various possible effects on the radiation belts.

Ces travaux de recherche présentent une modélisation/Simulation du Test BCI (Bulk Current Injection) sous contrainte RTCA – DO 160, test de qualification des équipements très contraignant en termes de coûts et délais. Lors de sa réalisation, il présente aussi beaucoup de disparités dont il est parfois difficile d’identifier les sources et de les maîtriser lors du test avec une maquette physique. La simulation présente tout son intérêt dans l’étude de ces phénomènes (qui peuvent avoir un impact non moins significatif sur les résultats de test) mais aussi la répétabilité des essais.Dans un premier temps, une méthode de modélisation du couplage pince d’injection de courant et câbles est établie qui tient compte de l’évolution en fonction de la fréquence du noyau de ferrite du transformateur RF (Pince de courant) et des paramètres linéiques des câbles. Deux modèles sont principalement proposés dans ces travaux :- Un modèle générique, modèle circuit constitué uniquement d’éléments passifs RLC et élaboré (sous SPICE) à partir de la mesure des paramètres S. Ce modèle fait apparaitre la zone de couplage entre pince et câbles au secondaire.- Un modèle magnétique, macro-modèle développé sous le logiciel Flux2D. Les paramètres géométriques du modèle sont renseignés à partir de la connaissance des dimensions de la pince (diamètres intérieur /extérieur, longueur) et des câbles (diamètres/longueurs). Les paramètres physiques de la pince de courant particulièrement la perméabilité magnétique complexe du noyau de ferrite est obtenue à partir de la mesure du coefficient de réflexion au port d’entrée de la pince et extraction en post-traitement.Les validations dans le domaine fréquentiel ont été effectuées avec une bonne corrélation entre simulations et mesures dans la bande BCI [10 kHz – 400 MHz]. Ces résultats obtenus ont permis l'élaboration d'un modèle complet du test BCI (sous l’outil logiciel PAM-CEM/CRIPTE) qui tient compte d’un toron aéronautique complexe et de l’EST (Équipement Sous Test modélisé au laboratoire Ampère de Lyon). Il est constitué du générateur de perturbation (qui fait office de pince d’injection de courant), du modèle du toron de câbles (constitué de paires torsadées blindées, de paires non-blindées, …) et de l’EST (Équipement Sous Test) dans la bande [10 kHz – 400 MHz]. La bonne concordance entre simulations et mesures laisse présager une utilisation par les avionneurs ou équipementiers pour des études paramétriques concernant le test BCI (influence de la disposition des câbles, queue de cochon, longueur toron, disposition de l’EST par rapport au plan de masse, …) et/ou pour une virtualisation dans une phase de pré-qualification des équipements.Mots clés : CEM (Compatibilité ElectroMagnétique), Test BCI (Bulk Current Injection), Modélisation/Simulation, Norme aéronautique DO 160. / This work presents a modeling/simulation approach of BCI (Bulk Current Injection) test under constraint RTCA - DO 160. This qualification test of equipment is very constraining in terms of cost and deadline. During the test, there are also many disparities for which it is difficult to identify sources (and control them) with a physical test setup. The simulation is of interest in the study of phenomena (which can have negative impacts on test results) but also the repeatability of tests.First, a method of modeling for the probe/cables coupling is established which takes into account the variation with frequency of the RF transformer (current probe) of the magnetic ferrite core and the linear parameters of cables (skin/ proximity effects). Two models are proposed in this work:- A generic model which is made up solely of passive elements RLC and elaborated (with SPICE software) from the measurement of S-parameters. It shows the coupling zone between probe and cables (secondary winding).- A magnetic macro-model developed with the Flux2D software. Its geometrical parameters are defined from dimensions of the probe (inner/outer diameter, length) and cables (diameters / length). Physical parameters of the current probe, particularly the complex magnetic permeability of the ferrite core, are obtained from measurement of the S-parameter at the input port of the probe and post-treatment extraction.Frequency domain validations were performed with a good correlation between simulations and measurements in the BCI band ([10 kHz - 400 MHz]).These results led to the development of a complete virtual BCI test (with PAM-CEM / CRIPTE software), which take into account an aeronautic complex harness and a DUT (Device Under Test which is modeled at Ampère laboratory). It consists of disturbance generator, harness model (consisting of shielding twisted cables, no shielding cables, etc.) and DUT (Device Under Test) in the band [10 kHz - 400 MHz].The good correlation between simulations and measurements suggests a use by the aircraft manufacturers or equipment manufacturers for parametric studies about BCI test (uncertainties related to cable positions, pigtail, cable length, DUT position with respect to the ground plane, ...) and /or for virtualization in a pre-qualification phase of the equipment.Keywords: EMC (ElectroMagnetic Compatibility), BCI (Bulk Current Injection) test, Modeling/Simulation, DO 160 aeronautic standard.