This study presents a comparative performance evaluation between two propulsion architectures for lightweight CS-23 class aircraft: a battery-only configuration and a hybrid-electric system integrating a Proton Exchange Membrane Fuel Cell (PEMFC) with a lower-capacity lithium-ion battery pack. Both configurations are modeled and simulated in MATLAB/Simulink under an identical mission profile comprising take-off, climb, cruise, and descent phases. The results indicate that although both systems deliver around 20 kWh of total energy, the hybrid configuration distributes energy more efficiently—supplying about 85% of the power through a 20 kW PEMFC, with a 4 kWh battery handling peak demands. Compared to the battery-only setup, the hybrid system exhibits a reduced final battery depletion (SoC of 0.46 vs. near full discharge) and smoother power handling, leading to lower battery stress and potentially extended operational lifespan. These results underscore the benefits of hybrid-electric architectures in improving endurance and system reliability in the context of electrified aviation.
Numerical Assessment of Hybrid PEMFC–Battery vs. Battery-Only Propulsion for Sustainable Light Aviation
Movahedian, Abolfazl;Frosina, Emma
2025-01-01
Abstract
This study presents a comparative performance evaluation between two propulsion architectures for lightweight CS-23 class aircraft: a battery-only configuration and a hybrid-electric system integrating a Proton Exchange Membrane Fuel Cell (PEMFC) with a lower-capacity lithium-ion battery pack. Both configurations are modeled and simulated in MATLAB/Simulink under an identical mission profile comprising take-off, climb, cruise, and descent phases. The results indicate that although both systems deliver around 20 kWh of total energy, the hybrid configuration distributes energy more efficiently—supplying about 85% of the power through a 20 kW PEMFC, with a 4 kWh battery handling peak demands. Compared to the battery-only setup, the hybrid system exhibits a reduced final battery depletion (SoC of 0.46 vs. near full discharge) and smoother power handling, leading to lower battery stress and potentially extended operational lifespan. These results underscore the benefits of hybrid-electric architectures in improving endurance and system reliability in the context of electrified aviation.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
