Este trabalho apresenta a aplicação da teoria de Controle Robusto H-infinito em modelo não linear de sistema de suspensão ativa com Atuador Tubular de Ímã Permanente (ATIP). Os principais objetivos na aplicação dos sistemas ativos de suspensão são a obtenção de melhores níveis de conforto do usuário e dirigibilidade do veículo em relação aos sistemas de suspensão passivo e semi-ativo, e a manutenção dos limites de deslocamento da suspensão. Inicialmente, são apresentados os modelos de suspensão ativa de um quarto de carro e carro completo, utilizados respectivamente como planta para o projeto dos controladores H-infinito e como modelo para as simulações dos sistemas de suspensão em malha fechada. Em seguida, o conjunto de controladores H-infinito e desenvolvido, baseado em especificações de projeto definidas, para posterior avaliação e comparação dos sistemas projetados. Verificações de robustez dos sistemas de suspensão ativos, utilizando-se da Análise-µ como ferramenta de avaliação, são feitas em conjunto com as análises de desempenho de cada sistema. A avaliação de desempenho dos sistemas é realizada tanto no domínio do tempo (avaliando-se angulações, velocidades, acelerações, defexões e energia do sistema) quanto no domínio da frequência (através da análise de densidade espectral de potência, ou Power Spectral Density (PSD), das acelerações verticais do veículo e do esforço de controle do atuador). A excitação do sistema é realizada por meio de distúrbios impostos às posições das rodas, dos tipos determinístico e estocástico, representativos de condições reais da aplicação de um veículo. O conjunto de controladores desenvolvido neste trabalho apresenta resultados satisfatórios para distúrbios de entrada do tipo determinísticos e estocásticos, com ganhos de desempenho dos sistemas de suspensão ativa em relação ao sistema passivo de referência de até 34; 92% para a métrica de avaliação do conforto do usuário, de 17; 23% para a métrica da manutenção da dirigibilidade, e de 43; 48% e 30; 10% para as métricas das acelerações dos ângulos de arfagem e de rolagem da carroceria, respectivamente. / This work presents the application of the H-infinity robust control theory into a non-linear model of active suspension system with a Tubular Permanent Magnet Actuator (TPMA). The main objectives in the application of the active suspension systems are the achievement of greater levels of comfort to the user and of road holding for the vehicle, when compared to the passive and semi-active suspension systems, besides the maintenance of suspension displacement limits. Initially are presented the active suspension models of a quarter-car and of a full-car, used respectively as a plant for the design of the H-infinity controllers and as a model for the simulations of the closed loop suspension systems. In the sequel, the controllers are developed, based on properly defined specifications, for further evaluation and comparison among the systems designed. Robustness verications of the active suspension systems, using the µ-Analysis as assessment tool, are performed together with the performance analysis of each system. The performance evaluation of the systems is performed both in the time domain (assessing angles, speeds, accelerations, dections and the energy of the system) and in the frequency domain (through the analysis of Power Spectral Density (PSD) of vertical accelerations of the vehicle and the control efort of the actuator). The excitation of the system is carried out by means of disturbances imposed to the vertical wheel\'s positions. Those disturbances are of deterministic and stochastic types, which are representatives of real working conditions of the vehicle. The set of controllers developed in this work presents satisfactory results for both deterministic and stochastic input disturbances, with performance gains of the active suspension systems in relation to the passive system of reference up to 34; 92%, 17; 23%, 43; 48% and 30; 10% respectively to the assessment metrics of user comfort, handling maintenance and acceleration of the pitch and roll angles of the chassis.

Este trabalho apresenta a aplicação da teoria de Controle Robusto H-infinito em modelo não linear de sistema de suspensão ativa com Atuador Tubular de Ímã Permanente (ATIP). Os principais objetivos na aplicação dos sistemas ativos de suspensão são a obtenção de melhores níveis de conforto do usuário e dirigibilidade do veículo em relação aos sistemas de suspensão passivo e semi-ativo, e a manutenção dos limites de deslocamento da suspensão. Inicialmente, são apresentados os modelos de suspensão ativa de um quarto de carro e carro completo, utilizados respectivamente como planta para o projeto dos controladores H-infinito e como modelo para as simulações dos sistemas de suspensão em malha fechada. Em seguida, o conjunto de controladores H-infinito e desenvolvido, baseado em especificações de projeto definidas, para posterior avaliação e comparação dos sistemas projetados. Verificações de robustez dos sistemas de suspensão ativos, utilizando-se da Análise-µ como ferramenta de avaliação, são feitas em conjunto com as análises de desempenho de cada sistema. A avaliação de desempenho dos sistemas é realizada tanto no domínio do tempo (avaliando-se angulações, velocidades, acelerações, defexões e energia do sistema) quanto no domínio da frequência (através da análise de densidade espectral de potência, ou Power Spectral Density (PSD), das acelerações verticais do veículo e do esforço de controle do atuador). A excitação do sistema é realizada por meio de distúrbios impostos às posições das rodas, dos tipos determinístico e estocástico, representativos de condições reais da aplicação de um veículo. O conjunto de controladores desenvolvido neste trabalho apresenta resultados satisfatórios para distúrbios de entrada do tipo determinísticos e estocásticos, com ganhos de desempenho dos sistemas de suspensão ativa em relação ao sistema passivo de referência de até 34; 92% para a métrica de avaliação do conforto do usuário, de 17; 23% para a métrica da manutenção da dirigibilidade, e de 43; 48% e 30; 10% para as métricas das acelerações dos ângulos de arfagem e de rolagem da carroceria, respectivamente. / This work presents the application of the H-infinity robust control theory into a non-linear model of active suspension system with a Tubular Permanent Magnet Actuator (TPMA). The main objectives in the application of the active suspension systems are the achievement of greater levels of comfort to the user and of road holding for the vehicle, when compared to the passive and semi-active suspension systems, besides the maintenance of suspension displacement limits. Initially are presented the active suspension models of a quarter-car and of a full-car, used respectively as a plant for the design of the H-infinity controllers and as a model for the simulations of the closed loop suspension systems. In the sequel, the controllers are developed, based on properly defined specifications, for further evaluation and comparison among the systems designed. Robustness verications of the active suspension systems, using the µ-Analysis as assessment tool, are performed together with the performance analysis of each system. The performance evaluation of the systems is performed both in the time domain (assessing angles, speeds, accelerations, dections and the energy of the system) and in the frequency domain (through the analysis of Power Spectral Density (PSD) of vertical accelerations of the vehicle and the control efort of the actuator). The excitation of the system is carried out by means of disturbances imposed to the vertical wheel\'s positions. Those disturbances are of deterministic and stochastic types, which are representatives of real working conditions of the vehicle. The set of controllers developed in this work presents satisfactory results for both deterministic and stochastic input disturbances, with performance gains of the active suspension systems in relation to the passive system of reference up to 34; 92%, 17; 23%, 43; 48% and 30; 10% respectively to the assessment metrics of user comfort, handling maintenance and acceleration of the pitch and roll angles of the chassis.

<p>Flight Control Systems are often designed in linearization points over a flight envelope and it must be proven to clearance authorities that the system works for different parameter variations and failures all over this envelope. </p><p>In this thesis µ-analysis is tried as a complement for linear analysis in the frequency plane. Using this method stability can be guaranteed for all static parameter combinations modelled and linear criteria such as phase and gain margins and most unstable eigenvalue can be included in the analysis. A way of including bounds on the parameter variations using parameter dependent Lyapunov functions is also tried. </p><p>To perform µ-analysis the system must be described as a Linear Fractional Transformation (LFT). This is a way of reformulating a parameter dependent system description as an interconnection of a nominal linear time invariant system and a structured parameter block. </p><p>A linear and a rational approximation of the system are used to make LFTs. These methods are compared. Four algorithms for calculation of the upper and lower bounds of µ are evaluated. The methods are tried on VEGAS, a SAAB research aircraft model. </p><p>µ-analysis works quite well for linear clearance. The rational approximation LFT gives best results and can be cleared for the criteria mentioned above. A combination of the algorithms is used for best results. When the Lyapunov based method is used the size of the problem grows quite fast and, due to numerical problems, stability can only be guaranteed for a reduced model.</p>

Flight Control Systems are often designed in linearization points over a flight envelope and it must be proven to clearance authorities that the system works for different parameter variations and failures all over this envelope. In this thesis µ-analysis is tried as a complement for linear analysis in the frequency plane. Using this method stability can be guaranteed for all static parameter combinations modelled and linear criteria such as phase and gain margins and most unstable eigenvalue can be included in the analysis. A way of including bounds on the parameter variations using parameter dependent Lyapunov functions is also tried. To perform µ-analysis the system must be described as a Linear Fractional Transformation (LFT). This is a way of reformulating a parameter dependent system description as an interconnection of a nominal linear time invariant system and a structured parameter block. A linear and a rational approximation of the system are used to make LFTs. These methods are compared. Four algorithms for calculation of the upper and lower bounds of µ are evaluated. The methods are tried on VEGAS, a SAAB research aircraft model. µ-analysis works quite well for linear clearance. The rational approximation LFT gives best results and can be cleared for the criteria mentioned above. A combination of the algorithms is used for best results. When the Lyapunov based method is used the size of the problem grows quite fast and, due to numerical problems, stability can only be guaranteed for a reduced model.

Cette thèse présente une méthodologie de conception et d’évaluation de lois de commande pour projectiles guidés, au moyen d’un prototype placé dans une soufflerie via un support autorisant plusieurs degrés de liberté en rotation. Ce dispositif procure un environnement permettant à la fois de caractériser expérimentalement le comportement de la munition et d’évaluer les performances des lois de commande dans des conditions réalistes, et est mis en œuvre pour l’étude d’autopilotes de tangage et de lacet, à vitesse fixe et à vitesse variable, pour un prototype de projectile empenné piloté par canards. La modélisation d’un tel système aboutit à un modèle non-linéaire dépendant de nombreuses conditions de vol telles que la vitesse et des angles d’incidence. Les méthodes de séquencement de gain basées sur des linéarisations d’un modèle non-linéaire sont couramment employées dans l’industrie pour la commande de ce type de systèmes. A cette fin, le système est représenté au moyen d’une famille de modèles linéaires dont les paramètres sont directement estimés à partir de données recueillies sur le dispositif expérimental. L’observation du comportement à différents points de vol permet de considérer la vitesse de l’air comme unique variable de séquencement. La synthèse des différents contrôleurs est réalisée au moyen d’une méthode H∞ multi-objectifs à ordre et structure fixes, afin de garantir la stabilité et la robustesse du système vis-à-vis d’incertitudes liées à la variation du point de fonctionnement. Ces lois de commande sont alors validées au moyen d’analyses de robustesse, puis par leur implémentation sur le dispositif expérimental. Les résultats obtenus lors d’essais en soufflerie correspondent aux simulations numériques et sont conformes aux spécifications attendues. / This work presents a novel methodology for flight control law design and evaluation, using a functional prototype installed in a wind tunnel by the means of a support structure allowing multiple rotational degrees of freedom. This setup provides an environment allowing experimental characterization of the munition’s behavior, as well as for flight control law evaluation in realistic conditions. The design and validation of pitch and yaw autopilots for a fin-stabilized, canard-guided projectile is investigated, at fixed and variable airspeeds. Modeling such a system leads to a nonlinear model depending on numerous flight conditions such as the airspeed and incidence angles. Linearization-based gain scheduling techniques are widely employed in the industry for controlling this class of systems. To this end, the system is represented with a family of linear models whose parameters are directly estimated from experimentally collected data. Observation of the projectile’s behavior for different operating points indicates the airspeed can be considered as the only scheduling variable. Controller synthesis is performed using a multi-objective, fixed-order, fixed-structure H∞ technique in order to guarantee the stability and robustness of the closed-loop against operating point uncertainty. The obtained control laws are validated with robustness analysis techniques and are then implemented on the experimental setup, where wind-tunnel tests results correlate with numerical simulations and conform to the design specifications.