An Aircraft Hybrid Electric Propulsion Model Experimentally Validated

In this paper a Matlab/Simulink model of a Hybrid Electric Propulsion System (HEPS) for aircraft application is presented. An Electric Machine (EM) is mechanically coupled to Internal Combustion Engine (ICE) via a one-way bearing to obtain a parallel hybrid propulsion configuration. Numerical modelling and experimental validation of the system have been carried out; the experimental data were acquired on propulsion prototype installed on test bench at University of Naples Federico II. Before implementing the entire powertrain model in Matlab/Simulink environment, the experimental characterizations of single systems, ICE and EM, in terms of performance and efficiency have been done. Furthermore, the proposed model also contains a generic dynamic sub model of rechargeable lithium-ion batteries that represents the most popular types of accumulators currently used in propulsion systems. The entire model was validated by the experimental data obtained during a quick mission of aircraft simulated on test bench. To confirm the good matching between experimental and simulated data of proposed model, two different statistical indexes are also evaluated. The results of the experimental and simulated activities show the completely feasibility of the designed hybrid electric propulsion system architecture. Finally, the model provides a smart, easy, fast tool to implement any control strategies to enhance fuel consumption, CO2 and pollutant emissions, which are the main goals of the hybrid solutions of transportation sector.