WorldCat Identities

Arzelier, Denis

Overview
Works: 19 works in 45 publications in 3 languages and 365 library holdings
Roles: Thesis advisor, Author, Publishing director, Opponent, Other, htt
Publication Timeline
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Most widely held works by Denis Arzelier
S-variable approach to LMI-based robust control by Yoshio Ebihara( )

16 editions published between 2000 and 2015 in English and Italian and held by 330 WorldCat member libraries worldwide

This book shows how the use of S-variables (SVs) in enhancing the range of problems that can be addressed with the already-versatile linear matrix inequality (LMI) approach to control can, in many cases, be put on a more unified, methodical footing. Beginning with the fundamentals of the SV approach, the text shows how the basic idea can be used for each problem (and when it should not be employed at all). The specific adaptations of the method necessitated by each problem are also detailed. The problems dealt with in the book have the common traits that: analytic closed-form solutions are not available; and LMIs can be applied to produce numerical solutions with a certain amount of conservatism. Typical examples are robustness analysis of linear systems affected by parametric uncertainties and the synthesis of a linear controller satisfying multiple, often conflicting, design specifications. For problems in which LMI methods produce conservative results, the SV approach is shown to achieve greater accuracy. The authors emphasize the simplicity and easy comprehensibility of the SV approach and show how it can be implemented in programs without difficulty so that its power becomes readily apparent. The S-Variable Approach to LMI-Based Robust Control is a useful reference for academic control researchers, applied mathematicians and graduate students interested in LMI methods and convex optimization and will also be of considerable assistance to practising control engineers faced with problems of conservatism in their systems and controllers
Robustesse en performance et en stabilité des systèmes linéaires incertains : une approche quadratique by Denis Arzelier( Book )

4 editions published in 1992 in French and held by 6 WorldCat member libraries worldwide

CETTE THESE A POUR SUJET LA COMMANDE ROBUSTE DES SYSTEMES DYNAMIQUES LINEAIRES INCERTAINS CONTINUS, DECRITS PAR DES EQUATIONS D'ETAT. LE PROBLEME DE LA COMMANDE ROBUSTE EST ABORDE ICI PAR LE BIAIS DU CONCEPT DE STABILISABILITE QUADRATIQUE QUI ETABLIT L'EXISTENCE D'UNE FONCTION DE LYAPUNOV QUADRATIQUE POUR LE SYSTEME. EN PREMIER LIEU, LE PROBLEME DES PERFORMANCES EST ABORDE A TRAVERS LE PLACEMENT ROBUSTE DES POLES DU SYSTEME EN BOUCLE FERMEE DANS UN SECTEUR DU DEMI-PLAN COMPLEXE GAUCHE. EN SECOND LIEU, LE PROBLEME DE LA COMMANDE ROBUSTE PAR RETOUR DE SORTIE EST ENVISAGE. LES CAS DU RETOUR DE SORTIE STATIQUE ET DYNAMIQUE ONT ETE EGALEMENT TRAITES. FINALEMENT, UNE AUTRE CLASSE DE MODELES LINEAIRES EST CONSIDEREE: LES MODELES SINGULIERS. DES PROCEDURES DE STABILISATION ONT ETE DEVELOPPEES SUR CES MODELES CERTAINS ET QUELQUES ELEMENTS DE ROBUSTESSE ONT ETE INTRODUITS SUR LES MODELES SINGULIERS INCERTAINS
La synthèse multi-objectif( Book )

2 editions published between 2006 and 2007 in French and held by 6 WorldCat member libraries worldwide

FORMULATION GENERIQUE DE PROBLEMES EN ANALYSE ET COMMANDE ROBUSTE PAR DES FONCTIONS DE LYAPUNOV DEPENDANT DES PARAMETRES by Dimitri Peaucelle( Book )

2 editions published in 2000 in French and held by 3 WorldCat member libraries worldwide

CETTE THESE PORTE SUR LA COMMANDE ROBUSTE DES SYSTEMES. LA ROBUSTESSE CARACTERISE L'INVARIANCE DE PROPRIETES DE STABILITE ET DE PERFORMANCE VIS A VIS DES INEVITABLES INCERTITUDES AFFECTANT LE MODELE. LE PROBLEME DE COMMANDE EST D'AMELIORER ET/OU DE GARANTIR LES PROPRIETES ROBUSTES. LES MODELES CONSIDERES SONT LINEAIRES A TEMPS INVARIANT. LES INCERTITUDES SONT PARAMETRIQUES REELLES STRUCTUREES ET INTERVIENNENT SOUS FORME RATIONNELLE. LES CLASSES D'INCERTITUDES POLYTOPIQUES ET DISSIPATIVES SONT PLUS PARTICULIEREMENT PRISES EN COMPTE. LES PROPRIETES ETUDIEES SONT PRINCIPALEMENT LA STABILITE ROBUSTE, LE REJET DES PERTURBATIONS (COUT GARANTI ROBUSTE) ET LE COMPORTEMENT TRANSITOIRE (LOCALISATION DES POLES). POUR CES PROPRIETES NOUS PROPOSONS DANS UN PREMIER TEMPS DES METHODES D'ANALYSE PUIS DES METHODES DE SYNTHESE DE CORRECTEURS. LES OUTILS THEORIQUES UTILISES SONT ISSUS DE LA THEORIE DE LYAPUNOV ET DE LA SEPARATION TOPOLOGIQUE. DE MANIERE A GARANTIR LES PERFORMANCES AVEC LE MOINS DE PESSIMISME POSSIBLE, NOUS PROPOSONS DE FAIRE APPEL A DES FONCTIONS DE LYAPUNOV DEPENDANT DES PARAMETRES. COMME ON ATTACHE UNE IMPORTANCE A LA MISE EN UVRE NUMERIQUE, DES METHODES ISSUES DU CADRE DE LA STABILITE QUADRATIQUE, PLUS PESSIMISTES MAIS MOINS DEMANDEUSES EN CAPACITE DE CALCUL SONT EGALEMENT PROPOSEES. LA FORMULATION VOLONTAIREMENT UNIFIEE DES DIFFERENTS PROBLEMES MET EN EVIDENCE LES SOURCES DE PESSIMISME. TOUTES LES METHODES PROPOSEES SONT FORMULEES EN TERMES D'INEGALITES MATRICIELLES LINEAIRES (LMI) DONT LA MISE EN UVRE NUMERIQUE EST DESORMAIS CLASSIQUE. LES RESULTATS DE RECHERCHE SONT ILLUSTRES SUR DES EXEMPLES
Méthodes d'analyse et de synthèse robustes pour les systèmes linéaires périodiques by Christophe Farges( Book )

2 editions published in 2006 in French and held by 2 WorldCat member libraries worldwide

Cette thèse porte sur la commande robuste des systèmes linéaires périodiques qui constituent une classe particulière de systèmes variant dans le temps. Des dynamiques périodiques apparaissent dans de nombreux domaines des sciences de l'ingénieur tels que l'aéronautique, l'espace ou les systèmes de télécommunication. Des méthodes systématiques pour l'analyse et la synthèse robuste de ces systèmes sont proposées. Le cadre de travail choisi est celui de la théorie de Lyapunov et fait appel principalement à des outils numériques de type inégalités matricielles linéaires (LMI). La robustesse est envisagée de manière duale par la prise en compte d'incertitudes pouvant non seulement affecter le système à commander mais également le correcteur lui même. Ce dernier problème est traité par la synthèse d'ensembles convexes de correcteurs assurant un certain niveau de performances garanties vis-à-vis du système bouclé. La question de la structure temporelle du correcteur est également posée. Le correcteur doit il nécessairement être de même périodicité que le système? Est-il possible de réduire le nombre de paramètres à mémoriser? Pour répondre à ces différentes questions, nous avons défini la classe des correcteurs périodiques structurés dans le temps et développé des méthodes de synthèse adaptées. Les résultats théoriques sont illustrés sur le problème du maintien à poste autonome d'un satellite en orbite basse consistant à maintenir un satellite sur une orbite de référence excentrique malgré les différentes forces perturbatrices pouvant l'en écarter (frottement atmosphérique, effet de la distribution non-sphérique de la masse de la Terre). Différentes lois de commande minimisant certains critères de performances tels que la quantité de carburant consommée ou l'influence d'accélérations perturbatrices sont calculées. Leur qualité est ensuite évaluée à l'aide de simulations non-linéaires
Stratégies de maintien à poste pour un satellite géostationnaire à propulsion tout électrique by Clément Gazzino( Book )

2 editions published in 2018 in French and held by 2 WorldCat member libraries worldwide

Pour mener à bien leur mission, les satellites de télécommunications doivent rester à la verticale d'un même point de la Terre, sur une orbite dite géostationnaire, pour laquelle la période de révolution des satellites sur leur orbite est identique à la période de rotation de la Terre sur elle-même. Cependant, à cause des perturbations orbitales, les satellites tendent à s'en éloigner, et il est alors nécessaire de concevoir des stratégies de commande pour les maintenir dans un voisinage de cette position de référence. Du fait de leur grande valeur de poussée, les systèmes à propulsion chimique ont largement été utilisés, mais aujourd'hui les systèmes à propulsion électrique avec leur grande impulsion spécifique sont des alternatives viables pour réduire la masse d'ergols du satellite, et ainsi le coût au lancement, ou allonger la durée de vie du satellite, ce qui permettrait de limiter l'encombrement dans l'espace. Cependant, l'utilisation d'un tel système propulsif induit des contraintes opérationnelles issues en partie du caractère limité de la puissance électrique disponible à bord. Ces contraintes sont difficiles à prendre en compte dans la transcription du problème de maintien à poste en un problème de contrôle optimal à consommation minimale avec contraintes sur l'état et le contrôle. Ce manuscrit propose deux approches pour résoudre ce problème de commande optimale. La première, basée sur le développement et l'exploitation de conditions nécessaires d'optimalité, consiste à découper le problème initial en trois sous-problèmes pour former une méthode de résolution à trois étapes. La première étape permet de résoudre un problème de maintien à poste expurgé des contraintes opérationnelles, tandis que la deuxième, initialisée par le résultat de la première, produit une solution assurant le respect de ces dernières contraintes. La troisième étape permet d'optimiser la valeur des instants d'allumage et d'extinction des propulseurs dans le cadre du formalisme des systèmes à commutation. La seconde approche, dite " directe ", consiste à paramétrer le profil de commande par une fonction binaire et à le discrétiser sur l'horizon temporel de résolution. Les contraintes opérationnelles sont ainsi facilement transcrites en contraintes linéaires en nombres entiers. Après l'intégration numérique de la dynamique, le problème de contrôle optimal se résume à un problème linéaire en nombres entiers. Après la résolution du problème de maintien à poste sur un horizon court d'une semaine, le problème est résolu sur un horizon long d'un an par résolutions successives sur des horizons courts d'une durée de l'ordre de la semaine. Des contraintes de fin d'horizon court doivent alors être ajoutées afin d'assurer la faisabilité de l'enchaînement des problèmes sur l'horizon court constituant le problème sur l'horizon long
Opérations de proximité en orbite : évaluation du risque de collision et calcul de manoeuvres optimales pour l'évitement et le rendez-vous by Romain Serra( Book )

2 editions published in 2015 in French and held by 2 WorldCat member libraries worldwide

This 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
Modélisation et guidage robuste et autonome pour le problème de rendez-vous orbital by Mounir Kara-Zaitri( Book )

2 editions published in 2010 in French and held by 2 WorldCat member libraries worldwide

In 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
Guidance and robust control methods for the approach phase between two orbital vehicles with coupling between translational and rotational motions by Laura Sofia Urbina Iglesias( Book )

2 editions published in 2017 in English and held by 2 WorldCat member libraries worldwide

The techniques related to formation flying and proximity operations of autonomous satellites belong to the most significant and challenging operational space technologies of the last years. In particular, they require full mastery of the close-range rendezvous and observation phases by an active satellite with a passive satellite, station or debris. The development of efficient and safe associated GNC systems relies on the knowledge of a dynamic model that achieves a good trade-off between low complexity and sufficient inclusion of the main dynamic and kinematic characteristics of this type of systems.The first part of this thesis is devoted to the development of a unified modeling of the relative coupled dynamics between a cooperative chaser satellite and a non-cooperative target satellite. Indeed, when two satellites are close to each other, they can no longer be treated as point masses because their shape and size affect the relative motion between the decentralized points, leading to a translational-attitude motions coupling. This development is addressed in a progressive way: the relative nonlinear translational motion is described under Keplerian assumptions in the target's orbital reference frame, as well as the associated linearized model. Then, the nonlinear relative attitude model is presented by means of the Euler-Rodrigues parameters. Finally, the dual quaternion formalism is used to obtain the relative translational and attitude coupled model. The modeling phase concerning the linear relative translational motion has allowed us to highlight certain coordinates transformations leading to an interesting characterization of the chaser's periodic trajectories and thus, to propose a first type of control law for the close-phase rendezvous and observation phases.All along this work, we consider a chaser satellite equipped with chemical thrusters under the classical hypothesis of impulsive thrusts. This type of dynamic systems gathering continuous dynamics and impulsive control naturally belongs to a particular class of dynamical hybrid systems. Several hybrid control laws are then proposed in order to stabilize the chaser on a periodic reference trajectory close to the target. The stability and convergence properties of these different laws are analysed and several numerical simulations show the strengths and weaknesses of each controller in terms of performance indices such as convergence time, consumption and safety constraints. In a second step, additional operational constraints (line-of-sight constraints for example) are taken into account by imposing a rectilinear (glideslope) direction to the chaser. This trajectory requires the chaser satellite to follow a straight line in any direction of the local reference frame and connecting the current location of the chaser to its final destination. Under the impulsive propulsion assumptions, the results in the literature for this type of approach have been generalized to elliptic orbits by identifying a new formulation of the problem including useful degrees of freedom, which allow minimizing the fuel consumption while controlling the humps of the trajectory outside the glideslope line by enclosing it in a user-defined approach corridor. Guidance laws are therefore synthetized via the solution of an SDP optimisation problem in the general case and via a linear programming when considering standard cases like the V-bar or R-bar approaches
A two-stage disk pole assignment of linear uncertain singularly perturbed (systems)( )

1 edition published in 1995 in English and held by 1 WorldCat member library worldwide

Linear matrix inequalities in control( Book )

1 edition published in 2006 in English and held by 1 WorldCat member library worldwide

Robust pole assignment by dynamic output feedback by Germain Garcia( )

1 edition published in 1995 in English and held by 1 WorldCat member library worldwide

Guidage et pilotage d'un remorqueur magnétique spatial by Emilien Fabacher( )

1 edition published in 2016 in English and held by 1 WorldCat member library worldwide

Satellite tugging can be undertaken for various reasons: de-orbiting or reorbiting,necessary in the case of satellites at the end-of-life, or for instance to finalise launches,in which case this manoeuvre would increase the capacity of launchers' upper stages. Severalmeans can be considered to modify the orbit of a target satellite by tugging it with anothersatellite. Contact-less concepts are interesting, as they provide a way to avoid standardisedinterfaces and hazardous docking phases. They also help to prevent the creation of new debrisby reducing the risk of collision. In this thesis, we suggest using magnetic forces to tug the target. Indeed many satellites, especially in Low Earth Orbit, are equipped with Magnetic Torque Bars used for attitudecontrol. A chaser satellite equipped with a powerful magnetic dipole could hence generateforces on the target. However, creating a force between two magnetic dipoles automaticallycreates torque on both of them. Therefore, the feasibility of magnetic tugging is a priori notassured, considering that applying constant torques on both satellites would not be acceptable
A LMI solution for disk pole allocation with H<2> guaranteed cost by Germain Garcia( )

1 edition published in 1995 in English and held by 1 WorldCat member library worldwide

Passivity preserving balanced reduction for the finite and infinite dimensional port Hamiltonian systems by Yongxin Wu( )

1 edition published in 2015 in English and held by 1 WorldCat member library worldwide

In this thesis we have developed different structure preserving reduction methods for finite and infinite dimensional port Hamiltonian systems by using a balanced model reduction approach. In the first part we have defined a descriptor representation of port Hamiltonian systems with constraints. The balanced realization of the descriptor system has been used for reducing the port Hamiltonian descriptor system and conserving explicitly the constraint equations. In the second part, conditions have been derived on the weighting matrices of the LQG control problem such that the dynamical LQG controller is passive and has a port Hamiltonian realization. Two passive LQG control design methods have been suggested and one of them allows us to define a LQG balanced realization. Based on this realization, the effort constraint method has been used to reduce the LQG balanced port Hamiltonian system and obtain a reduced order passive LQG controller. In this way the closed-loop system is derived from the interconnection of 2 port Hamiltonian systems, hence the Hamiltonian structure has been preserved. In the third part, the proceeding results have been extended to a class of infinite dimensional port Hamiltonian system with bounded input operator. A passive LQG control design method for infinite dimensional port Hamiltonian system has been derived as by Control by Interconnection (CbI). Based on the balanced realization associated with this passive LQG control design, a finite dimensional approximation has been achieved and a reduced order passive LQG controller has been derived. As a consequence, the system in closed-loop with this reduced order LQG controller again admits a port Hamiltonian structure and satisfies the passivity
Modélisation et guidage robuste et autonome pour le problème de rendez-vous orbital by Mounir Kara-Zaitri( )

1 edition published in 2011 in French and held by 1 WorldCat member library worldwide

In 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
Synthèse de correcteurs robustes périodiques à mémoire et application au contrôle d'attitude de satellites par roues à réaction et magnéto-coupleurs by Jean-François Trégouët( )

2 editions published in 2012 in French and held by 1 WorldCat member library worldwide

Les travaux présentés dans ce mémoire constituent une contribution à la conception de méthodes systématiques pour l'analyse et la commande de systèmes périodiques et incertains. Une partie importante de cette thèse est également consacrée au contrôle d'attitude de satellites dont la dynamique se prête naturellement à une représentation sous forme de modèles périodiques soumis à des incertitudes. La première partie propose une présentation unifiée des résultats d'analyse et de synthèse de modèles périodiques et incertains à temps-discret via des méthodes basées sur des inégalités linéaires matricielles (LMI) et en s'appuyant sur la théorie de Lyapunov. Par la suite, l'accent est mis sur une nouvelle classe de correcteurs périodiques à mémoire pour lesquels l'entrée de commande est construite en utilisant l'historique des états du système conservés en mémoire. Des exemples numériques démontrent que ces nouveaux degrés de liberté permettent de repousser les limites des performances robustes. La seconde partie s'intéresse aux aspects de périodicité et de robustesse du contrôle d'attitude de satellite rencontrés notamment lors de l'utilisation des magnéto-coupleurs. Ces actionneurs s'appuient sur le champ géomagnétique variant périodiquement le long de l'orbite du satellite. Différentes stratégies de commande sont mises en œuvre et comparées entre elles avec le souci constant de tenir compte des principales limitations des actionneurs. Cette démarche conduit à une nouvelle loi de commande périodique régulant le moment cinétique des roues à réactions sans perturber le contrôle d'attitude dont l'effort de commande est réparti sur l'ensemble des actionneurs
Robust performance analysis with LMI-based methods for real parametric uncertainty via parameter dependent lyapunov fuctions by Demitri Peaucelle( )

1 edition published in 2001 in English and held by 1 WorldCat member library worldwide

Numerical methods for hybrid control and chance-constrained optimization problems by Achille Sassi( )

1 edition published in 2017 in English and held by 1 WorldCat member library worldwide

This thesis is devoted to the analysis of numerical methods in the field of optimal control, and it is composed of two parts. The first part is dedicated to new results on the subject of numerical methods for the optimal control of hybrid systems, controlled by measurable functions and discontinuous jumps in the state variable simultaneously. The second part focuses on a particular application of trajectory optimization problems for space launchers. Here we use some nonlinear optimization methods combined with non-parametric statistics techniques. This kind of problems belongs to the family of stochastic optimization problems and it features the minimization of a cost function in the presence of a constraint which needs to be satisfied within a desired probability threshold
 
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S-variable approach to LMI-based robust control
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