A solid oxide fuel cell-based power system is modeled and simulated to investigate both power management and controllability issues experienced while subjecting the system to the typical power requirements of a small aircraft. Initially, the fuel cell stack is assumed to operate along one characteristic curve, thus isolating the power management study to the system’s powertrain components. Electrical converters transfer dc power from the fuel cell to usable ac power for an electric motor-driven propeller. To avoid oversizing, the fuel cell stack is designed to operate near its maximum power limit during aircraft cruising, while a battery is employed as an alternative source to provide additional power beyond the cruising kilowatt requirement (e.g., takeoff or maneuvering).
Fuel Cell-Based Powertrain System Modeling and Simulation for Small Aircraft Propulsion Applications
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Brinson, T. E., Ren, W., Ordonez, J. C., Luongo, C. A., and Baldwin, T. (August 17, 2009). "Fuel Cell-Based Powertrain System Modeling and Simulation for Small Aircraft Propulsion Applications." ASME. J. Fuel Cell Sci. Technol. November 2009; 6(4): 041012. https://doi.org/10.1115/1.3006303
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