Fornaro, Enrico (2023) Management strategies for aircraft hybrid propulsion stystem and experimental assesment. [Tesi di dottorato]
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| Tipologia del documento: | Tesi di dottorato |
|---|---|
| Lingua: | English |
| Titolo: | Management strategies for aircraft hybrid propulsion stystem and experimental assesment |
| Autori: | Autore Email Fornaro, Enrico enrico.fornaro@unina.it |
| Data: | 11 Dicembre 2023 |
| Numero di pagine: | 156 |
| Istituzione: | Università degli Studi di Napoli Federico II |
| Dipartimento: | Ingegneria Industriale |
| Dottorato: | Ingegneria industriale |
| Ciclo di dottorato: | 36 |
| Coordinatore del Corso di dottorato: | nome email Grassi, Michele michele.grassi@unina.it |
| Tutor: | nome email Cardone, Massimo [non definito] |
| Data: | 11 Dicembre 2023 |
| Numero di pagine: | 156 |
| Parole chiave: | aircraft, hybrid, propulsion system, ECMS, efficiency, CO2 reduction |
| Settori scientifico-disciplinari del MIUR: | Area 09 - Ingegneria industriale e dell'informazione > ING-IND/07 - Propulsione aerospaziale Area 09 - Ingegneria industriale e dell'informazione > ING-IND/08 - Macchine a fluido Area 09 - Ingegneria industriale e dell'informazione > ING-IND/09 - Sistemi per l'energia e l'ambiente Area 09 - Ingegneria industriale e dell'informazione > ING-IND/12 - Misure meccaniche e termiche |
| Depositato il: | 29 Dic 2023 15:26 |
| Ultima modifica: | 09 Mar 2026 14:39 |
| URI: | http://www.fedoa.unina.it/id/eprint/15671 |
Abstract
The significant reduction of CO2 and NOx emissions, as well as aircraft noise, is becoming an increasingly urgent target for many aeronautical agencies to be achieved by 2050. Therefore, many changes will be needed in the aviation propulsion industry in the coming years. In this context, hybrid-electric propulsion systems (HEPS) could be a good compromise for reducing emissions and noise while having a lighter propulsive architecture than a fully electric system. In the present work, an experimental investigation has been carried out on a hybrid-electric propulsion system (HEPS) for aircraft application. The experimental data has been used to validate the HEPS model designed in Matlab/Simulink consisting of a point-mass aircraft dynamical model coupled with a map-based approach for the simulation of the powertrain components, i.e., propeller, internal combustion engine, electric machine, and battery. The simulated results showed good matching to the experimental ones. Moreover, the proposed model demonstrates its capability and flexibility to predict the global HEPS dynamical behavior and performance. Moreover, an adaptive supervisor controller is integrated into the model to minimize the equivalent fuel consumption during the flight mission. The proposed method has been applied to an eight-sit civil utility aircraft employed for repetitive short-range missions typical of air taxi applications. The analysis shows that thanks to the proper selection of the Degree of Hybridization and the optimal control strategy, a 6% CO2 reduction is achieved compared to the conventional “Fully-Thermal” configuration. Moreover, the reduction reaches a significant amount of 31% when a plug-in architecture is adopted. Moreover, in this work, the adaptive supervisor, developed in Matlab/Simulink, is tested in real-time in the engine test laboratory on the real HEPS, evaluating the control capability and the real-time management of the engines. For this purpose, a short-duration mission has been chosen to represent the typical aviation maneuvers generally performed by a pilot (i.e., Take-off, climb, cruise, and landing).
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