Rozprawy doktorskie na temat „Véhicules spatiaux – Systèmes de télécommande”
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Couty, Charles-Emmanuel. "Développement de nouveaux concepts d’antennes de télémétrie et télécommunications pour lanceurs et satellites en orbite basse". Electronic Thesis or Diss., Limoges, 2024. http://www.theses.fr/2024LIMO0016.
Pełny tekst źródłaProduction of an antenna for Ariane 6, the special feature of which is that it has a modular orientation to ensure continuous communication with the base station. The originality of the work concerns the design and production of a phase shifter. The work mainly involves design (simulations) and characterisation. Manufacturing is carried out by an industrial subcontractor
Glumineau, Alain. "Solutions algebriques pour l'analyse et le controle des systemes non lineaires". Nantes, 1992. http://www.theses.fr/1992NANT2046.
Pełny tekst źródłaMetni, Najib. "Asservissement visuel, suivi de trajectoire et estimation d'orientation d'un engin volant à voilures tournantes". Nice, 2006. http://www.theses.fr/2006NICE4088.
Pełny tekst źródłaVTOL (Vertical Takeoff and Landing) flying vehicles are non-linear, unstable and complex systems in particular during quasi-stationary flight mode, they present a strongly coupled dynamics. Thus, we were interested throughout this thesis to the problems of visual servoing and orientation estimation of VTOL robots in order to obtain good performances for their automatic control. The thesis is divided into two parts: We developed a visual servoing control strategy of a VTOL engine in hovering mode. This control law is based on the robust techniques of Backstepping, allowing the limitation of the orientation to small values. Then, we worked out a control law of tracking a predefined trajectory. The direction of the gravity vector exists even in the definition of the visual errors. Therefore, it is crucial to get a precise estimation of this direction vector. We used inertial measurements to elaborate an estimator for the gravity direction and another estimator for an independent direction. From these two directions the orientation matrix was restored. The vector of gyroscope bias is also estimated. Another original aspect of this work is the conception of a third estimator for the total orientation matrix, this estimator guarantees that the matrix of orientation remains in the SO(3) group. The control strategies and the estimators were validated by results from simulations and experiments on the HoverEye vehicle from Bertin Technologies
Roynette, Eliott. "Optimisation de la conception du design du harnais de commande des véhicules spatiaux". Thesis, Toulouse, ISAE, 2018. http://www.theses.fr/2018ESAE0011/document.
Pełny tekst źródłaSixty years ago, on October 4, 1957, Sputnik, the first man-made artificial satellite, was sent into space. Its only function is to emit a radio beep at frequencies of 20 and 40 MHz to demonstrate the space power of the USSR. Since then, satellites have been multiple and their missions have diversified. Today, the missions of the satellites are so varied that some leave Earth's orbit. We speak in the case of probes, even if, in the rest of this thesis, they will be included in the term "satellite". The best-known satellite mission of the general public is the discovery of the universe and interplanetary exploration with satellite satellites such as the Hubble International Space Telescope or probes such as Rosetta, Voyager 1 and 2, ... nevertheless nowadays Although space exploration remains a major issue for humanity, most satellites have smaller missions that have a significant impact on economic and political life. The satellites in question today have two goals: defense and commercial. In both cases the satellites can be divided into two distinct groups: observation satellites and telecommunication satellites. To operate all these satellites, use an electrical harness. The electrical harness includes all the cables present in the satellite and which does not carry any customer data. As part of this we are interested in optimizing the design of the electrical harness of satellites
Grall, Antoine. "Contrôle de la rentrée d'une navette". Compiègne, 1992. http://www.theses.fr/1992COMPD546.
Pełny tekst źródłaGateau, Thibault. "Supervision de mission pour une équipe de véhicules autonomes hétérogènes". Thesis, Toulouse, ISAE, 2012. http://www.theses.fr/2012ESAE0038/document.
Pełny tekst źródłaMany autonomous robots with specific control oriented architectures have already been developed worldwide.The advance of the work in this field has led researchers wonder for many years to what extent robots would be able to be integrated into a team consisting of autonomous and heterogeneous vehicles with complementary functionalities. However, robot cooperation in a real dynamic environment under unreliable communication conditions remains challenging, especially if these autonomous vehicles have different individual control architectures.In order to address this problem, we have designed a decision software architecture, distributed on each vehicle.This decision layer aims at managing execution and at increasing the fault tolerance of the global system. The mission plan is assumed to be hierarchically structured. ln case of failure detection, the plan repair is done as locally as possible, based on the hierarchical organization.This allows us to restrict message exchange only between the vehicles concerned by the repair process. Knowledge formalisation is also a part of the study permitting the improvement of interoperability between team members. It also provides relevant information all along mission execution, from initial planning computation to plan repair in this multirobot context. The feasibility of the system has been evaluated by simulations and real experiments thanks to the Action project (http://action.onera.fr/welcome/)
Benziane, Lotfi. "Contributions à l'estimation et à la commande d'attitude de véhicules aériens autonomes". Thesis, Versailles-St Quentin en Yvelines, 2015. http://www.theses.fr/2015VERS015V/document.
Pełny tekst źródłaNowadays, we see a growing popularity of the use of Unmanned Aerial Vehicles (UAV) ofespecially Vertical Take-Off and Landing (VTOL) type. One of the most known VTOL is thequadrotor or Quadcopter which is probably the most used one as a research platform. Thisthesis deal with attitude control and estimation techniques applied to a rigid body movingin 3D space such as Quadcopter VTOL. The first contribution of this thesis is the design ofa new class of complementary linear-like filters allowing the fusion of inertial vector measurementswith angular velocity measurements and combined with algebraic algorithms asTRIAD, QUEST etc. to give an efficient attitude estimation solution. This class of filtersallows several possibilities of implementation such as the order of the filters which can bechosen high in order to reduce more the measurement noise and the form of the filters thatcan be direct or passive and the ability to take into account the possible gyro bias. Lyapunovanalysis shows the global asymptotic convergence of the estimation errors to zero. The sameprinciple of data fusion is used for the proposed new attitude control law in which the complementaryfilters were included to reduce the effect of measurement noise. The obtainedcontroller ensures almost global stability of the desired equilibrium point; it represents thesecond contribution of this thesis. The third contribution takes into consideration an interestingspecial case, where instantaneous measurements of attitude and angular velocity areunavailable. A first order linear auxiliary system based directly on vector measurements isused in an observer-like system to handle the luck of angular velocity. The proposed controllerensures almost global asymptotic stability of the trajectories to the desired equilibriumpoint. Detailed sets of experiments were done to validate the obtained results
Zerar, Madjid. "CONTRIBUTION À LA CARACTÉRISATION LPV D'UNE CLASSE DE SYSTÈMES NON LINÉAIRES POUR LA SYNTHÈSE DE LOIS DE POURSUITE ROBUSTE. APPLICATION À UN SYSTÈME SPATIAL". Phd thesis, Université Sciences et Technologies - Bordeaux I, 2006. http://tel.archives-ouvertes.fr/tel-00012135.
Pełny tekst źródłaPham, Bach Van. "Système de navigation absolue pour l'atterrissage d'une sonde interplanétaire". Toulouse, ISAE, 2010. https://tel.archives-ouvertes.fr/tel-00559626.
Pełny tekst źródłaSilva, Costa Raphaël. "Nouvelles approches pour la synthèse de systèmes polyazotés de type HEDM". Thesis, Lyon, 2018. http://www.theses.fr/2018LYSE1300/document.
Pełny tekst źródłaThe research carried during this PhD aims to synthesis new compounds with polynitrogen-backbone suitable for spacecraft or military propulsion. Indeed, the actual spacecraft uses a technology which is reliable, but with some limitation with their energetic efficiency and to satisfy the REACH regulation. It is necessary, for the Europeans launcher to stay at the first position in public or private satellites launch world wild, to find new and more efficient propellant. So, this work was focused on the synthesis of “HEDM” (High Energetic Density Material) compounds, which possess much higher propulsive features than the actual propellants. This could lead to a breakthrough in spacecraft propulsion in the next 30 years.For this PhD work two compounds of interest were identified: the pentazolate anion, which is an all nitrogen aromatic compound with a formula of N5-, and the cyclopentazan, which is an original polynitrogen compound with a formula of N5H5. First, we focused our work on the synthesis of various arylpentazoles followed by oxidative or reductive ways which lead to the pentazolate anion. Secondly, we synthesised and the studied the stability of polynitrogen-based compound, triazanes and azimines. Those compounds were then used in trials of cycloadditions which will lead to the cyclopentazan. Finally, we studied various way of complexing our polynitrogen-compound with various metallic complexes
Rojas-Ramirez, Belem Isabel. "Modeling and control of aerial vehicles using teleoperation with input delay". Thesis, Compiègne, 2020. http://www.theses.fr/2020COMP2568.
Pełny tekst źródłaUnmanned Aerial Vehicles (UAVs) are receiving increasing interest from industry and academia due to their wide application in search and rescue, infrastructure inspection, surveillance, among others. This thesis focuses on research in the area of teleoperation systems for quadrotor vehicles. Throughout this thesis, a teleoperation system for a quadrotor vehicle was developed. In this system, the user interface is based on a virtual telepresence approach. Control algorithms were developed and implemented within the master and slave systems. The first part of this thesis consists of developing mathematical models of the dynamics of a quadrotor aircraft. Most works currently found in the literature for quadrotors are based on classical approaches such as Euler angles. These representations can lead to problems such as discontinuities, singularities, gimbal-locks, and highly non-linear equations. An alternative to these classical representations are unit quaternions. These have the advantages of the lack of singularities and gimbal lock effects. The second part of this work was dedicated to the development of a quadrotor teleoperation system. This system consists of a virtual user interface in a local environment and a quadrotor in a remote environment. A User Datagram Protocol (UDP) communication was used to communicate both environments. The user manipulates a virtual drone in the local environment and a real drone follows the position and orientation references in a remote environment. The user receives virtual feedback on the states of the real vehicle in the virtual environment. Results of the implementation of the proposed teleoperation system in real time are presented. The last part of this thesis addresses the delay problem in the teleoperation system. Delays due to system latency and the distance between environments were modeled as a delayed control input. Then, a predictor-based controller was developed in order to maintain the stability of a drone’s flight. This approach was applied to the classical Euler- Lagrange model and to the quaternion-based model in order to analyze performance. Simulations of both models with delayed inputs are presented
Morio, Vincent. "Contribution au développement d’une loi de guidage autonome par platitude : application à une mission de rentrée atmosphérique". Thesis, Bordeaux 1, 2009. http://www.theses.fr/2009BOR13797/document.
Pełny tekst źródłaThis thesis deals with the design of an autonomous guidance law based on flatness approach for atmospheric reentry vehicles. The problematic involved by the design of an autonomous guidance law relates to the global organization, the integration and the management of relevant data up to the mastering of the spacecraft during the re-entry mission. The autonomous guidance law proposed in this dissertation is based on flatness concept, in order to perform onboard processing so as to locally assign autonomy and responsibility to the vehicle, thus exempting the ground segment from "low level" operational tasks, so that it can ensure more efficiently its mission of global coordination. The first part of the manuscript deals with the formal characterization of flat outputs for nonlinear systems governed by ordinary differential equations, as well as for linear time-delay systems. Constructive algorithms are proposed in order to compute candidate flat outputs within a standard formal computing environment. In the second part of the manuscript, a global and generic reentry trajectory replanning methodology is proposed in order to provide a fault-tolerance capability to the guidance law, when facing single/multiple control surface failures that could occur during the critical phases of an atmospheric reentry mission. In addition, a superellipsoidal annexion method is proposed so as to convexify the optimal control problem described in the flat outputs space. The proposed guidance law is then applied step by step to an atmospheric reentry mission for the US Space Shuttle orbiter STS-1
Kara-Zaitri, Mounir. "Modélisation et guidage robuste et autonome pour le problème de rendez-vous orbital". Toulouse 3, 2010. http://thesesups.ups-tlse.fr/1026/.
Pełny tekst źródłaIn this thesis, two fundamental steps of the orbital rendezvous are studied: the relative navigation and the minimum-fuel guidance. The first part is devoted to the modeling of spacecraft relative motion under linear assumptions. A comprehensive bibliography review and a novel method of relative motion model design are given in this part as well as a mapping between the various state space variables forms. These developments are undertaken in order to provide reliable and accurate navigation tools in the presence of orbital perturbations. The guidance is considered in the second part through the development of several algorithms for solving the fixed-time rendezvous problem. Each algorithm is developed using different theoretical tools such as indirect methods for solving optimal control problems based on the maximum principle or direct techniques exploiting the discretizing of optimal control problems and linear programming. Various objectives are considered through the use of these tools, including minimization of fuel consumption and robustness toward the navigation errors. Other algorithms are designed in order to improve their practical implementation thanks to the use of orbital mechanics theory. A set of validation tests and comparisons is made, where examples from academic literature and real missions are solved using the different algorithms. This is achieved in order to highlight the most relevant theoretical and practical aspects of the proposed algorithms
Gerst, Jan Dennis. "Investigation of magnetized radio frequency plasma sources for electric space propulsion". Phd thesis, Université d'Orléans, 2013. http://tel.archives-ouvertes.fr/tel-00977801.
Pełny tekst źródłaLefebvre, Mickael. "Gestion automatisée de l’énergie d’un avion de transport civil : application aux phases de descente et d’approche". Thesis, Toulouse, ISAE, 2012. http://www.theses.fr/2012ESAE0016.
Pełny tekst źródłaThe first year of thesis allowed to foreground two aspects of the energy management issue,namely the short term control and the long term control, respectively. The first issue was studied during the second year and ended with the proposition of a solution mixing both the airbrakes and engines. The second and last issue started with a preliminary study which consisted of computing an optimal slat/flap command sequence bringing the aircraft to theright energy level in approach while minimizing the use of engines and airbrakes. Then, this study was extended in order to take into account the regulation of engines and airbrakes aswell as vertical trajectory modification. Finally, this optimization-based solution has been integrated within an accurate real-time desktop simulator, tested with a human-machine interface, and then presented to flight test pilots for validation
Serra, Romain. "Opérations de proximité en orbite : évaluation du risque de collision et calcul de manoeuvres optimales pour l'évitement et le rendez-vous". Thesis, Toulouse, INSA, 2015. http://www.theses.fr/2015ISAT0035/document.
Pełny tekst źródłaThis thesis is about collision avoidance for a pair of spherical orbiting objects. The primary object - the operational satellite - is active in the sense that it can use its thrusters to change its trajectory, while the secondary object is a space debris that cannot be controlled in any way. Onground radars or other means allow to foresee a conjunction involving an operational space craft,leading in the production of a collision alert. The latter contains statistical data on the position and velocity of the two objects, enabling for the construction of a probabilistic collision model.The work is divided in two parts : the computation of collision probabilities and the design of maneuvers to lower the collision risk. In the first part, two kinds of probabilities - that can be written as integrals of a Gaussian distribution over an Euclidean ball in 2 and 3 dimensions -are expanded in convergent power series with positive terms. It is done using the theories of Laplace transform and Definite functions. In the second part, the question of collision avoidance is formulated as a chance-constrained optimization problem. Depending on the collision model, namely short or long-term encounters, it is respectively tackled via the scenario approach or relaxed using polyhedral collision sets. For the latter, two methods are proposed. The first one directly tackles the joint chance constraints while the second uses another relaxation called risk selection to obtain a mixed-integer program. Additionaly, the solution to the problem of fixed-time fuel minimizing out-of-plane proximity maneuvers is derived. This optimal control problem is solved via the primer vector theory
Hernandez, Lopezomoza Mario Andres. "Cadre de travail généralisé de compensation non-linéaire robuste : application à la rentrée atmosphérique". Thesis, Toulouse, ISAE, 2012. http://www.theses.fr/2012ESAE0022/document.
Pełny tekst źródłaThis thesis work is devoted to extending Nonlinear Dynamic Inversion (NDI) for a large scale of nonlinear systems while guaranteeing sufficient stability conditions. NDI has been studied in a wide range of applications, including aeronautics and aerospace. It allows to compute nonlinear control laws able to decouple and linearize a model at any operating point of its state envelope. However, this method is inherently non-robust to modelling errors and input saturations. Moreover, obtaining a quantifiable guarantee of the attained stability domain in a nonlinear control context is not a very straightforward task. Unlike standard NDI approaches, our methodology can be viewed as a generalized nonlinear compensation framework which allows to incorporate uncertainties and input saturations in the design process. Paralleling anti-windup strategies, the controller can be computed through a single multichannel optimization problem or through a simple two-step process. Within this framework, linear fractional transformations of the nonlinear closed-loop can be easily derived for robust stability analysis using standard tools for linear systems. The proposed method is tested for the flight control of a delta wing type reentry vehicle at hypersonic, transonic and subsonic phases of the atmospheric reentry. For this thesis work, a Flight Mechanics simulator including diverse external factors and modelling errors was developed in Simulink
Vaudolon, Julien. "Electric field determination and magnetic topology optimization in Hall thrusters". Thesis, Orléans, 2015. http://www.theses.fr/2015ORLE2026/document.
Pełny tekst źródłaElectric propulsion is facing new challenges. Recently, the launch of "all-electric" satellites has marked the debut of a new era. Going all-electric now appears as an interesting alternative to conventional systems for telecom operators. A laser spectroscopy technique was used during this research to investigate the ion velocity distribution dynamics. The different methods for determining the electric field in Hall thrusters were exposed. Two unstable ion regimes were identified and examined. Measurement uncertainties using electrostatic probes were assessed. Planar probed have been designed and tested. A thorough investigation of the influence of the magnetic field parameters on the performance of Hall thrusters was performed. The wall-less Hall thruster design was presented, and preliminary experiments have revealed its interest for the electric propulsion community
Mattei, Giovanni. "Robust nonlinear control : from continuous time to sampled-data with aerospace applications". Thesis, Paris 11, 2015. http://www.theses.fr/2015PA112025/document.
Pełny tekst źródłaThe dissertation deals with the problems of stabilization and control of nonlinear systems with deterministic model uncertainties. First, in the context of uncertain systems analysis, we introduce and explain the basic concepts of robust stability and stabilizability. Then, we propose a method of stabilization via state-feedback in presence of unmatched uncertainties in the dynamics. The recursive backstepping approach allows to compensate the uncertain terms acting outside the control span and to construct a robust control Lyapunov function, which is exploited in the subsequent design of a compensator for the matched uncertainties. The obtained controller is called recursive Lyapunov redesign. Next, we introduce the stabilization technique through Immersion \& Invariance (I\&I) as a tool to improve the robustness of a given nonlinear controller with respect to unmodeled dynamics. The recursive Lyapunov redesign is then applied to the attitude stabilization of a spacecraft with flexible appendages and to the autopilot design of an asymmetric air-to-air missile. Contextually, we develop a systematic method to rapidly evaluate the aerodynamic perturbation terms exploiting the deterministic model of the uncertainty. The effectiveness of the proposed controller is highlighted through several simulations in the second case-study considered. In the final part of the work, the technique of I\& I is reformulated in the digital setting in the case of a special class of systems in feedback form, for which constructive continuous-time solutions exist, by means of backstepping and nonlinear domination arguments. The sampled-data implementation is based on a multi-rate control solution, whose existence is guaranteed for the class of systems considered. The digital controller guarantees, under sampling, the properties of manifold attractivity and trajectory boundedness. The control law, computed by finite approximation of a series expansion, is finally validated through numerical simulations in two academic examples and in two case-studies, namely the cart-pendulum system and the rigid spacecraft