Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2006. / Narayanan Komerath, Committee Chair ; Lakshmi Sankar, Committee Member ; JVR Prasad, Committee Member ; Mark Costello, Committee Member ; A. Terrence Conlisk Jr., Committee Member.

Thesis (PhD)--University of Stellenbosch, 2006. / Bibliography. Also available via the Internet.

Thesis (Ph. D.)--Mechanical Engineering, Georgia Institute of Technology, 2008. / Dewey H. Hodges, Committee Member ; Olivier Bauchau, Committee Member ; Aldo A. Ferri, Committee Member ; Itzhak Green, Committee Member ; Jerry H. Ginsberg, Committee Chair.

Th. 3e cycle--Électronique--Lille 1, 1980. N°: 809.

Th. 3e cycle--Méc.--Nancy--I.N.P.L., 1982.

Made available in DSpace on 2014-06-11T19:27:14Z (GMT). No. of bitstreams: 0 Previous issue date: 2012-08-14Bitstream added on 2014-06-13T18:55:42Z : No. of bitstreams: 1 guirao_vs_me_ilha.pdf: 3586237 bytes, checksum: 945e594528c1e4e71d8ddb43d3bc1001 (MD5) / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / Fundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP) / Este trabalho trata do controle de vibrações em rotores utilizando mancais magnéticos ativos. Foram apresentadas simulações numéricas para o posicionamento ótimo de um atuador magnético utilizado para atenuar vibrações em rotor apoiado por mancais convencionais. O posicionamento ótimo do atuador foi implementado utilizando como função objetivo as normas H2 e H∞. Para modelar o rotor foi utilizado o método de elementos finitos (MEF) e a técnica de redução pseudo-modal para diminuir o esforço computacional durante o controle. As simulações mostraram que um bom posicionamento do atuador aliado ao controle LQR proporcionam grandes reduções dos níveis de vibração no rotor, quando comparado aos níveis de vibração do rotor original. Para a bancada de testes foram realizadas simulações adicionais, tendo em vista que o rotor experimental utiliza dois mancais magnéticos para levitar e controlar as vibrações. Foram apresentados os resultados de simulações de dois controladores LQR projetados com os dados da bancada de testes utilizada nos experimentos. O primeiro controlador considera modelo de rotor flexível modelado pelo método de elementos finitos e reduzido com a técnica de redução pseudo-modal. O segundo controlador foi modelado considerando o rotor como sendo um corpo rígido. Os resultados experimentais foram confrontados com os resultados de simulação e com os resultados obtidos do controlador do fabricante que forneceu a bancada / This paper deals with vibration control of rotors using active magnetic bearings. Numerical simulations were presented for the optimal positioning of a magnetic actuator used to attenuate vibrations in rotor supported by conventional bearings. The optimal positioning of the actuator was implemented using as objective function the norm H2 e H∞. To model the rotor was used finite element method (FEM) and the pseudo-modal reduction technique to reduce computational effort during the control. The simulations showed that a good positioning actuator combined to the control LQR provide great reductions in the levels of vibration in the rotor, compared the vibration of the original rotor. For the test rig were realized adittional simulations, in view of the rotor experimental uses two magnetic bearings for levitating and control the vibrations. Were present the results of two simulations designed LQR controllers with data from the test rig used in the experiments. The first controller model considers flexible rotor modeled by finite element method and reduced with the pseudo-modal reduction technique. The second controller is modeled considering the rotor as a rigid body. The experimental results were compared with simulation results and the results obtained from the controller manufacturer who supplied the test rig

Les méthodes d'identification dites sous-espace sont largement utilisées pour la caractérisation des modes propres et la surveillance des structures mécaniques. Elles ont fait leurs preuves pour les systèmes dont la dynamique est invariante dans le temps. Elles ne sont, toutefois, pas adaptées à des systèmes à rotors comme les hélicoptères et les éoliennes qui, de part leurs parties tournantes, sont périodiques dans le temps. Le but de cette thèse est d'étendre le champ d'application de ces méthodes à cette classe particulière de systèmes. Tout d'abord, un algorithme qui permet d'identifier certaine structure modale, dite de Floquet, est proposée. Ensuite, une étude de sensibilité est réalisée dans le but de quantifier les incertitudes, liées aux bruits ou à d'autres facteurs, sur les paramètres modaux identifiés. Enfin et partant de l'algorithme d'identification, une méthode de détection d'instabilité est développée. Cette méthode est basée sur la définition d'un résidu, fonction des paramètres modaux, et la surveillance d'un changement éventuel de ce résidu qui correspond à une déviation vers un régime instable. Ces méthodes ont été appliquées à des modèles numériques et à des données expérimentales. / Subspace identification methods are widely used for caracterizing modal param-eters and for vibration monitoring of mechanical structures. They were shown powerful for the so-called linear time-invariant systems. However, they are not adapted to rotating sys-tems such as helicopters and wind turbines, which are inherently time-periodic systems. The goal of this thesis is to extend the applicability of these methods to this particular class of systems. First, a new identification algorithm is suggested. This algorithm permits to iden-tify the so-called Floquet modal structure. Then, a sensitivity study is conducted in order to quantify uncertainties, related to noises and other sources, about the identified modal param-eters. Finally and based on the suggested identification algorithm, a method for instability detection is developed. The main feature of this method is to define some residual, which is function of modal parameters, then to detect an eventual change over it which means a possible deviation toward an unstable regime. The suggested methods were applied to both numerical and experimental data.

A thesis submitted to the Faculty of Engineering, University of the Witwatersrand, Johannesburg, in fulfillment of the requirements for the degree of Master of Science in Engineering. / The use of advanced composite materials in helicopter rotor systems offers opportunities for improvements in aerodynamic geometry, performance, weight, damage tolerarice, maintenance and operating costs. Technical aspects of the design and analysis and the-practical aspects of the manufacture of a composite rotor system are discussed herein. The rotor system was compared to an existing conventional teetering rotor system, in order to establish the viability of the new composite rotor system, This rotor system reduced the number of components by 55% and the manufacturing time by half, due to the simplicity of the design and lay up procedure, thus making the system economically more viable. The mass was predicted to within 1% of that achieved in practice and gave a mass advantage of 50.5% over the conventional rotor. Static tests identified the failure modes and stress concentration points, while. the comparative hover tests showed the system to have ±20% less drag. [Abbreviated Abstract. Open document to view full version] / AC2017

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