Performance analysis of fuel cell hybrid-electric regional aircraft based on hydrogen/helium co-cooling

This paper presents a fuel cell hybrid electric propulsion system (FCHEPS) that integrates hydrogen fuel cell, cryogenic cooling, and superconducting technology, specifically designed for modern twin-engine turboprop regional aircraft. A parametric modeling approach was applied to key components, including hydrogen fuel cells, superconducting motors, and liquid hydrogen tanks. Additionally, a micro-channel plate hydrogen-helium heat exchanger (HX) was developed to maintain the optimal inlet temperature for the fuel cell and to cool cryogenic components. Energy management strategies based on state machine (SM) and equivalent consumption minimization strategy (ECMS) were developed to achieve optimal power distribution. Simulation results across cruise and emergency mission profiles validated the effectiveness of the powertrain configuration, analysis model and energy management strategies. The ECMS method demonstrated minimal fuel consumption and maximum energy conversion efficiency, making it particularly suitable for scenarios with frequent power demand fluctuations.