This Open Platform for Limit Protection guides the open design of maneuver limit protection systems in general, and manned, rotorcraft, aerospace applications in particular. The platform uses three stages of limit protection modules: limit cue creation, limit cue arbitration, and control system interface. A common set of limit cue modules provides commands that can include constraints, alerts, transfer functions, and friction. An arbitration module selects the best limit protection cues and distributes them to the most appropriate control path interface. This platform adopts a holistic approach to limit protection whereby it considers all potential interface points, including the pilots visual, aural, and tactile displays; and automatic command restraint shaping for autonomous limit protection. For each functional module, this thesis guides the control system designer through the design choices and information interfaces among the modules. Limit cue module design choices include type of prediction, prediction mechanism, method of critical control calculation, and type of limit cue. Special consideration is given to the nature of the limit, particularly the level of knowledge about it, and the ramifications for limit protection design, especially with respect to intelligent control methods such as fuzzy inference systems and neural networks. The Open Platform for Limit Protection reduces the effort required for initial limit protection design by defining a practical structure that still allows considerable design freedom. The platform reduces lifecycle effort through its open engineering systems approach of decoupled, modular design and standardized information interfaces. Using the Open Platform for Limit Protection, a carefree maneuver system is designed that addresses: main rotor blade stall as a steady-state limit; hub moment as a transient structural limit; and pilot induced oscillation as a controllability limit. The limit cue modules in this system make use of static neural networks, adaptive neural networks, and fuzzy inference systems to predict these limits. Visual (heads up display) and tactile (force-feedback) limit cues are employed. The carefree maneuver system is demonstrated in manned simulation using a General Helicopter (GENHEL) math model of the UH-60 Black Hawk, a projected, 53 degree field of view for the pilot, and a two-axis, active sidestick for cyclic control.

The problem of designing control systems for entire plants is studied. A review of previous works, available techniques and current research challenges is presented, followed by the description of some theoretical tools to improve plantwide control, including the proposal of an augmented lexicographic multi-objective optimization procedure. With these, an augmented hierarchical plantwide control design technique and an optimal multi-objective technique for integrated control structure selection and controller tuning are proposed. The main contributions of these proposed techniques are the inclusion of system identification and optimal control tuning as part of the plantwide design procedure for improved results, support to multi-objective control specifications and support to any type of plant and controllers. Finally, the proposed techniques are applied to industrial benchmarks to demonstrate and validate its applicability. / O problema de projetar sistemas de controle para plantas inteiras é estudado. Uma revisão de trabalhos anteriores, técnicas disponíveis e atuais desafios de pesquisa é apresentada, seguida da descrição de algumas ferramentas teóricas para melhorar o controle plantwide, incluindo a proposta de um procedimento de otimização multi-objetivo lexicográfico aumentado. Com tais elementos, são propostas uma nova técnica hierárquica aumentada de projeto de sistemas de controle plantwide e uma técnica multi-objetivo para seleção de estrutura de controlador integrada à sintonia ótima do controlador. As principais contribuições das técnicas propostas são a inclusão de identificação de sistemas e sintonia ótima de controladores como parte do procedimento de projeto de controle plantwide para melhores resultados, suporte a especificações multi-objetivo e suporte a quaisquer tipos de plantas e controladores. Finalmente, as técnicas propostas são aplicadas a benchmarks industriais para demonstrar e validar sua aplicabilidade.

This master’s thesis deals with the implementation of existing algorithms of electric AC motor control in Matlab Simulink to LabVIEW Control Design and Simulation. The first part of the thesis treats with the deduction of a mathematical model of an asynchronous motor, permanent magnet synchronous motor and with the theory of vector control of AC motors. In the next part there is a brief guide to create simulation algorithms in LabVIEW environment and to create the model of a motor with EMI functions in language C. The last part contains the comparison of Matlab Simulink and LabVIEW simulation tools.

Cette thèse aborde l'estimation et la conception de commande de systèmes non linéaires à temps continu. Les méthodologies développées sont basées sur la représentation Takagi-Sugeno (TS) du modèle non linéaire par l'approche du secteur non-linéarité. Toutes les stratégies ont l'intention d'obtenir des conditions plus détendu. Les résultats présentés pour la conception de commande sont divisés en deux parties. La première partie est environ sur les modèles TS standard au titre des schémas de commande basés sur: 1) une fonction de Lyapunov quadratique (QLF); 2) une fonction de Lyapunov floue (FLF); 3) une fonction de Lyapunov intégrale de ligne (LILF); 4) un nouveau fonctionnelle de Lyapunov non-quadratique (NQLF). La deuxième partie concerne des modèles TS descripteurs. Deux stratégies sont proposées: 1) dans le cadre quadratique, des conditions basées sur une loi de commande général et quelques transformations de matrices; 2) une extension de l'approche non quadratique basée sur LILF utilisant un schéma de commande non-PDC et le lemme du Finsler; cette stratégie offre conditions sur la forme d’inégalité matricielles linéaires (LMI) dépendant des paramètres au lieu des contraintes sur la forme d’inégalité matricielles bilinéaires (BMI) pour les systèmes de second ordre. D'autre part, le problème de l'estimation de l'état pour les systèmes non linéaires via modèles TS est également abordé considérant: a) le cas particulier où les vecteurs prémisses sont basées sur les variables mesurées et b) le cas général où les vecteurs prémisse peuvent être basés sur des variables non mesurées. Plusieurs exemples ont été inclus pour illustrer l'applicabilité des résultats obtenus. / This thesis addresses the estimation and controller design for continuous-time nonlinear systems. The methodologies developed are based on the Takagi-Sugeno (TS) representation of the nonlinear model via the sector nonlinearity approach. All strategies intend to get more relaxed conditions.The results presented for controller design are split in two parts. The first part is about standard TS models under control schemes based on: 1) a quadratic Lyapunov function (QLF); 2) a fuzzy Lyapunov function (FLF); 3) a line-integral Lyapunov functions (LILF); 4) a novel non-quadratic Lyapunov functional (NQLF). The second part concerns to TS descriptor models. Two strategies are proposed: 1) within the quadratic framework, conditions based on a general control law and some matrix transformations; 2) an extension to the nonquadratic approach based on a line-integral Lyapunov function (LILF) using non-PDC control law schemes and the Finsler’s Lemma; this strategy offers parameter-dependent linear matrix inequality (LMI) conditions instead of bilinear matrix inequality (BMI) constraints for second-order systems. On the other hand, the problem of the state estimation for nonlinear systems via TS models is also addressed considering: a) the particular case where premise vectors are based on measured variables and b) the general case where premise vectors can be based on unmeasured variables. Several examples have been included to illustrate the applicability of the obtained results.

In spite of significant reduction of cost associated with launching a spacecraft, launching deep space exploratory missions are yet to be accessible to most universities and researchers. A solution to testing scientific hypotheses and verifying technologies for space is the use of environmental chambers, also know as space simulators, - vacuum chambers, which replicate the space environment. The scope of this thesis project is to develop a thermal control system for a space simulator, which would replicate the environment on Mars, and allow for controlled carbon dioxide ice deposition experiments. The first part of the thesis looks at the climate on Mars, and the process behind the carbon dioxide ice cycle, gives a description of the systems in a space simulator. Then the requirements of a thermal system for the space simulator are stated. The second part of the thesis gives a brief overview of the previous solution attempts at the laboratory in Luleå University of Technology, and the manufacturing technologies required to make them. Based on that, a design justification is given. The thermal control system design section gives an overall design description, with detailed report on the iterative design of the sample holders, and thermal simulations results. Additive manufacturing is analyzed, as means of producing solid designs with the necessary performance targets. The overall cost of the designed thermal control system is calculated, and further work directions are proposed. The appendices include the literature used, the technical drawings for manufacturing and assembly of the thermal system, detailed budget calculations, and additional data from the thermal analysis.

Military helicopter operations require precise maneuverability characteristics for performance to be determined for the entire helicopter flight envelope. Historically, these maneuverability analyses are combinatorial in nature and involve human-interaction, which hinders their integration into conceptual design. A model formulation that includes the necessary quantitative measures and captures the impact of changing requirements real-time is presented. The formulation is shown to offer a more conservative estimate of maneuverability than traditional energy-based formulations through quantitative analysis of a typical pop-up maneuver. Although the control system design is not directly integrated, two control constraint measures are deemed essential in this work: control deflection rate and trajectory divergence rate. Both of these measures are general enough to be applied to any control architecture, while at the same time enable quantitative trades that relate overall vehicle maneuverability to control system requirements. The dimensionality issues stemming from the immense maneuver space are mitigated through systematic development of a maneuver taxonomy that enables the operational envelope to be decomposed into a minimal set of fundamental maneuvers. The taxonomy approach is applied to a helicopter canonical example that requires maneuverability and design to be assessed simultaneously. The end result is a methodology that enables the impact of design choices on maneuverability to be assessed for the entire helicopter operational envelope, while enabling constraints from control system design to be assessed real-time.

Un micro-réseau est un exemple prometteur d’évolution d’architecture de réseau qui consiste à regrouper les différents producteurs et consommateurs autour d'un réseau moyenne tension. Ce système hybride multi-source est donc composé d'au moins une unité de production décentralisée conventionnelle et éventuellement d'une unité de stockage et d’une unité de production basée sur des énergies renouvelables. L’utilisation de cette structure permet de réaliser une minimisation immédiate des pertes liées au transport de l’énergie, une fiabilité accrue de la fourniture et une possibilité de fournir une énergie d’une haute qualité. Dans ce mémoire, nous étudions un micro réseau reposant sur l’utilisation d’une turbine à gaz, d’une centrale photovoltaïque et d’une unité de stockage à base de supercondensateurs. Toutes ces sources sont couplées au micro réseau par des convertisseurs électroniques de puissance et sont interconnectées au gestionnaire central du micro-réseau. Des supervisions locales et une supervision centrale sont utilisées pour ce micro-réseau étudié afin de réaliser une optimisation de son fonctionnement. Par conséquence, la première partie de ce mémoire est consacrée à la formalisation d’une méthode permettant la conception systématique des supervisions locales et des dispositifs de commande des unités de production et de stockage. La seconde partie de cette thèse est consacrée à la gestion proprement dite de l’ensemble de ces moyens de production et de stockage en vue d’optimiser les services fournis aux micro-réseaux. Des résultats de la simulation et de l’expérimentation valident notre conception de la supervision du micro-réseau / A microgrid is a promising future network architecture which is coupling the various generators and consumers in a distribution network. This hybrid multi-source system is composed of at least one conventional generation unit and possibly a storage unit and/or a production unit based on renewable energies. Using this structure allows an immediate minimization of the losses by the energy transport, a greater reliability of power delivery and an ability to provide a high power quality energy. In this paper, we study a microgrid based on the use of a micro gas turbine, a photovoltaic array and supercapacitors. All these sources are coupled to the microgrid by power electronic converters and are interconnected to a microgrid central controller. Some local controllers and the microgrid central controller are used for the studied microgrid to achieve its operation optimization. Therefore, the first part of this thesis is devoted to establish a formalism method for a systematic design of local controllers. The second part of this thesis is devoted to the management of all these production and storage units, in order to optimize the microgrid operating. Simulation and testing results validate our design of the microgrid controllers

The aim of the diploma thesis is to create an algorithm by which it will be possible to devise management rules. These management rules will be able to advise a more efficient use of the hydroenergetic potential of reservoirs with run-of-river small hydro. The actual algorithm will be created with a view to maximizing the profit from the operation of the hydropower plant and using the time course of electricity prices on the market. The rules designed by algorithm will be tested in a simplified way in selected period using simulation model.

Cette thèse développe une nouvelle approche de contrôle pour les avions à échelle réduite. Les lois de commande proposées exploitent un modèle non linéaire simple mais pertinent des forces aérodynamiques appliquées à l’aéronef. Ils reposent sur une structure hiérarchique de contrôle non linéaires, et sont synthétisées sur la base d’analyse de stabilité et de convergence théoriques. Ils sont conçus pour fonctionner sur un large domaine de vol. En particulier, ils évitent les singularités associées à la paramétrisation de l'attitude et la direction de la vitesse. Dans un premier temps, le problème de stabilisation de trajectoires de référence est résolu en étendant la méthode du "thrust vectoring", utilisée pour les véhicules à voilure tournante, au cas des aéronefs à voilure fixe. Dans le cas des avions, le principal défi est de prendre en compte les forces aérodynamiques dans la conception des systèmes de commande. Afin de résoudre ce problème, le contrôle proposé est conçu et analysé sur la base du modèle de forces aérodynamique proposé. Le domaine d'utilisation de cette loi de commande est élargi et englobe les trajectoires d'équilibre (trim trajectories) qui sont classiquement utilisées dans la littérature. Cette solution est ensuite adaptée au problème de suivi de chemin, afin de concevoir des lois de guidage cinématique et de contrôle dynamique applicables à presque tout chemin 3D régulier. Les lois de contrôle proposées contiennent des termes intégraux qui robustifient le contrôle vis-à-vis de dynamiques non modélisées. Plusieurs problèmes pratiques sont adressés et les lois de commande proposées sont validées par des simulations du type "hardware-in-the-loop". Enfin, des résultats d'essais en vol illustrent la performance des lois de contrôle proposées. / The present thesis develops a new control approach for scale-model airplanes. The proposed control solutions exploit a simple but pertinent nonlinear model of aerodynamic forces acting on the aircraft. Nonlinear controllers are based on a hierarchical structure, and are derived on the basis of theoretical stability and convergence analyses. They are designed to operate on a large spectrum of operating conditions. In particular, they avoid the singularities associated with the parameterization of the attitude and the heading of the vehicle, and do not rely on a decoupling between longitudinal and lateral dynamics. First, the trajectory tracking problem is addressed by extending the thrust vectoring method used for small rotor vehicles to the case of fixed wing vehicles. In the case of airplanes, the main challenge is to take into account the aerodynamic forces in the design of control systems. In order to solve this problem, the proposed control is designed and analyzed on the basis of the proposed aerodynamic forces model. The flight envelope is thus broadened beyond trim trajectories which are classically used in the literature. This solution is then adapted to the path following problem, and kinematic guidance and dynamic control laws are developed within a single coherent framework that applies to almost any regular 3D path. The proposed control laws incorporate integral terms that robustify the control with respect to unmodelled dynamics. Several practical issues are addressed and the proposed control laws are validated via hardware-in-the-loop simulations. Finally, successful flight test results illustrate the soundness and performance of the proposed control laws.

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