No description available.

Line current distortion is an important issue to a high-power current source rectifier(CSR) system. There are two main challenges related to this issue. First, the CSR input LC resonance can be affected by the variation of the source inductance from the power system and the effects of the CSR DC side circuit, which may lead to a line current distortion higher than expected. Another challenge is that the traditional high-power CSR using Selective Harmonic Elimination (SHE) pulse-width modulation (PWM) technique attempts to eliminate certain harmonics in the PWM current, which limits its ability for line current harmonic control. To control the CSR line current harmonics, this thesis focuses on two aspects: 1) the analysis and design of CSR input filter to avoid unexpected input LC resonance, and 2) the development of a new PWM scheme that can compensate the effects of the grid voltage harmonics and DC link current ripples. The thesis work has been validated by simulations and on an experimental CSR prototype. / Power Engineering and Power Electronics

No description available.

Este trabalho apresenta um sistema de controle com o objetivo de atenuar as ondulações do torque eletromagnético considerando os harmônicos de quinta, sétima, décima primeira e décima terceira ordem da tensão do estator do Gerador de Indução Duplamente Alimentado (GIDA). Dessa maneira, propõe-se a utilização de controladores proporcional-integrativo vetoriais juntamente com um sistema de identificação dos componentes harmônicos da corrente do estator empregando a transformada discreta de Fourier. O trabalho aborda a influência dos harmônicos de quinta, sétima, décima primeira e décima terceira ordem da tensão do estator nos harmônicos da corrente do estator, nas ondulações do torque eletromagnético e nas potências ativa e reativa do estator. Resultados de simulação avaliam o controlador proposto em condições adversas: variações paramétricas e da frequência da rede, além da influência de atrasos na corrente do estator. Finalmente, resultados experimentais validam o sistema proposto. / This work presents a vector controller with the objective of reducing the electromagnetic torque and the active and reactive powers of the stator by means of control of the harmonics of the stator current in harmonic conditions of fifth, seventh, eleventh and thirteenth order of the stator voltage. The objective of the work is to propose a controller that uses two techniques already consolidated in the literature, proportional-integrative and discrete Fourier transform, besides being robust the main disadvantages of the existing harmonic controllers in the literature that are dependencies of the parameters of the machine and the Frequency of the network beyond the influence of the stator current delays on the harmonic controller. First, the influence of the fifth, seventh, eleventh, eleventh and thirteenth order harmonics of the stator voltage on the harmonics of the stator current and on the undulations of the electromagnetic torque and the active and reactive powers of the stator are studied. Next, simulation results evaluate the proposed controller under adverse conditions: parametric variations and the frequency of the network, besides the influence of stator current delays. Finally, experimental results validate the controller under conditions that the controller reference is nonzero.

Este trabalho apresenta um sistema de controle com o objetivo de atenuar as ondulações do torque eletromagnético considerando os harmônicos de quinta, sétima, décima primeira e décima terceira ordem da tensão do estator do Gerador de Indução Duplamente Alimentado (GIDA). Dessa maneira, propõe-se a utilização de controladores proporcional-integrativo vetoriais juntamente com um sistema de identificação dos componentes harmônicos da corrente do estator empregando a transformada discreta de Fourier. O trabalho aborda a influência dos harmônicos de quinta, sétima, décima primeira e décima terceira ordem da tensão do estator nos harmônicos da corrente do estator, nas ondulações do torque eletromagnético e nas potências ativa e reativa do estator. Resultados de simulação avaliam o controlador proposto em condições adversas: variações paramétricas e da frequência da rede, além da influência de atrasos na corrente do estator. Finalmente, resultados experimentais validam o sistema proposto. / This work presents a vector controller with the objective of reducing the electromagnetic torque and the active and reactive powers of the stator by means of control of the harmonics of the stator current in harmonic conditions of fifth, seventh, eleventh and thirteenth order of the stator voltage. The objective of the work is to propose a controller that uses two techniques already consolidated in the literature, proportional-integrative and discrete Fourier transform, besides being robust the main disadvantages of the existing harmonic controllers in the literature that are dependencies of the parameters of the machine and the Frequency of the network beyond the influence of the stator current delays on the harmonic controller. First, the influence of the fifth, seventh, eleventh, eleventh and thirteenth order harmonics of the stator voltage on the harmonics of the stator current and on the undulations of the electromagnetic torque and the active and reactive powers of the stator are studied. Next, simulation results evaluate the proposed controller under adverse conditions: parametric variations and the frequency of the network, besides the influence of stator current delays. Finally, experimental results validate the controller under conditions that the controller reference is nonzero.

<p>This dissertation investigates the optimal aerodynamic performance and design of conventional and coaxial helicopters in hover and forward flight using conventional and higher harmonic blade pitch control. First, we describe a method for determining the blade geometry, azimuthal blade pitch inputs, optimal shaft angle (rotor angle of attack), and division of propulsive and lifting forces among the components that minimize the total power for a given forward flight condition. The optimal design problem is cast as a variational statement that is discretized using a vortex lattice wake to model inviscid forces, combined with two-dimensional drag polars to model profile losses. The resulting nonlinear constrained optimization problem is solved via Newton iteration. We investigate the optimal design of a compound vehicle in forward flight comprised of a coaxial rotor system, a propeller, and optionally, a fixed wing. We show that higher harmonic control substantially reduces required power, and that both rotor and propeller efficiencies play an important role in determining the optimal shaft angle, which in turn affects the optimal design of each component. Second, we present a variational approach for determining the optimal (minimum power) torque-balanced coaxial hovering rotor using Blade Element Momentum Theory including swirl. We show that the optimal hovering coaxial rotor generates only a small percentage of its total thrust on the portion of the lower rotor operating in the upper rotor's contracted wake, resulting in an optimal design with very different upper and lower rotor twist and chord distributions. We also show that the swirl component of induced velocity has a relatively small effect on rotor performance at the disk loadings typical of helicopter rotors. Third, we describe a more refined model of the wake of a hovering conventional or coaxial rotor. We approximate the rotor or coaxial rotors as actuator disks (though not necessarily uniformly loaded) and the wake as contracting cylindrical vortex sheets that we represent as discrete vortex rings. We assume the system is axisymmetric and steady in time, and solve for the wake position that results in all vortex sheets being aligned with the streamlines of the flow field via Newton iteration. We show that the singularity that occurs where the vortex sheet terminates at the edge of the actuator disk is resolved through the formation of a 45 degree logarithmic spiral in hover, which results in a non-uniform inflow, particularly near the edge of the disk where the flow is entirely reversed, as originally hypothesized by previous authors. We also quantify the mutual interference of coaxial actuator disks of various axial spacing. Finally, we combine our forward flight optimization procedure and the Blade Element Momentum Theory hover optimization to form a variational approach to the multipoint aerodynamic design optimization of conventional and coaxial helicopter rotors. The resulting nonlinear constrained optimization problem may be used to map the Pareto frontier, i.e., the set of rotor designs for which it is not possible to improve upon the performance in one flight condition without degrading performance in the other. We show that for both conventional and coaxial rotors analyzed in hover and high speed flight, a substantial tradeoff in performance must be made between the two flight conditions. Finally, computational results demonstrate that higher harmonic control is able to improve the Pareto efficiency for both conventional and coaxial rotors.</p> / Dissertation