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Your search keyword '"Tartaglione G"' showing total 12 results
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12 results on '"Tartaglione G"'

2. Development of a concept and basis for the DEMO diagnostic and control system

Author

Biel, W., Ariola, M., Bolshakova, I, Brunner, K. J., Cecconello, Marco, Duran, I, Franke, Th, Giacomelli, L., Giannone, L., Janky, F., Krimmer, A., Luis, R., Malaquias, A., Marchiori, G., Marchuk, O., Mazon, D., Pironti, A., Quercia, A., Rispoli, N., El Shawish, S., Siccinio, M., Silva, A., Sozzi, C., Tartaglione, G., Todd, T., Treutterer, W., Zohm, H., Biel, W., Ariola, M., Bolshakova, I, Brunner, K. J., Cecconello, Marco, Duran, I, Franke, Th, Giacomelli, L., Giannone, L., Janky, F., Krimmer, A., Luis, R., Malaquias, A., Marchiori, G., Marchuk, O., Mazon, D., Pironti, A., Quercia, A., Rispoli, N., El Shawish, S., Siccinio, M., Silva, A., Sozzi, C., Tartaglione, G., Todd, T., Treutterer, W., and Zohm, H.

Abstract

An initial concept for the plasma diagnostic and control (D&C) system has been developed as part of European studies towards the development of a demonstration tokamak fusion reactor (DEMO). The main objective is to develop a feasible, integrated concept design of the DEMO D&C system that can provide reliable plasma control and high performance (electricity output) over extended periods of operation. While the fusion power is maximized when operating near to the operational limits of the tokamak, the reliability of operation typically improves when choosing parameters significantly distant from these limits. In addition to these conflicting requirements, the D&C development has to cope with strong adverse effects acting on all in vessel components on DEMO (harsh neutron environment, particle fluxes, temperatures, electromagnetic forces, etc.). Moreover, space allocation and plasma access are constrained by the needs for first wall integrity and optimization of tritium breeding. Taking into account these boundary conditions, the main DEMO plasma control issues have been formulated, and a list of diagnostic systems and channels needed for plasma control has been developed, which were selected for their robustness and the required coverage of control issues. For a validation and refinement of this concept, simulation tools are being refined and applied for equilibrium, kinetic and mode control studies.

Published
2022
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3. Development of a concept and basis for the DEMO diagnostic and control system

Author

Biel, W., primary, Ariola, M., additional, Bolshakova, I., additional, Brunner, K.J., additional, Cecconello, M., additional, Duran, I., additional, Franke, Th., additional, Giacomelli, L., additional, Giannone, L., additional, Janky, F., additional, Krimmer, A., additional, Luis, R., additional, Malaquias, A., additional, Marchiori, G., additional, Marchuk, O., additional, Mazon, D., additional, Pironti, A., additional, Quercia, A., additional, Rispoli, N., additional, Shawish, S. El, additional, Siccinio, M., additional, Silva, A., additional, Sozzi, C., additional, Tartaglione, G., additional, Todd, T., additional, Treutterer, W., additional, and Zohm, H., additional

Published
2022
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12. Nonlinear Dynamic Inversion and Neural Networks for a Tilt Tri-Rotor UAV

Author

Gaetano Tartaglione, Egidio D'Amato, Massimiliano Mattei, G. Di Francesco, Immacolata Notaro, D'Amato, E., Di Francesco, G., Notaro, I., Tartaglione, G., Mattei, M., IFAC, and Mattei, Massimiliano

Subjects
Engineering, Adaptive control, Nonlinear dynamic inversion, Artificial neural network, business.industry, Flight control, Inversion (meteorology), Control engineering, Unmanned aerial vehicle, Neural network, Inverse dynamics, Attitude control, Nonlinear system, Flight controller, Control and Systems Engineering, Control theory, Neural networks, business, Parametric statistics
Abstract

A small scale tri-rotor test bed with tilting propellers has been built to test flight control laws in view of the construction of a larger tilt rotor UAV. As a first step to achieve autonomous flight capabilities, a nonlinear dynamic inversion based flight controller is developed. This controller is designed on the basis of a time-scale principle with two levels. A lower level, fast control action, designed to achieve attitude control and stability goals, is driven by a higher level trajectory tracking control law. To achieve robust stability and performance in the presence of parametric variations and modelling uncertainties, an adaptive flight control law correction based on neural networks is investigated. A RBF neural network is implemented to mitigate the effects of imprecise inverse dynamics. The overall proposed flight controller performance are tested via numerical simulations on the mathematical model of the small scale tri-rotor. Preliminary results on the full tilt rotor are also shown. © 2015, IFAC (International Federation of Automatic Control) Hosting by Elsevier Ltd. All rights reserved

Published
2015
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