A power system (20, fig 2) for an aircraft (10, fig 1) includes a first fuel cell 202 configured to provide base power to one or more loads on the aircraft. The power system further includes a second fuel cell 214 configured to provide peak power to the one or more loads on the aircraft. The peak power can be a power exceeding the base power. The power system further includes an energy storage device 218 configured to provide transient power to the one or more loads on the aircraft. The transient power can be a power exceeding the peak power. The power system further includes a controller (290, fig 2) configured to control delivery of power from the first fuel cell 202, the second fuel cell 214, and the energy storage device 218 to the one or more loads on the aircraft. Methods (400, fig 4) for providing power to one or more loads on an aircraft are also provided.
Power system for more electric aircraft
2018-05-23
Patent
Electronic Resource
English
Power system characteristics for more electric aircraft
NTRS | 1993
|Power System Characteristics for More Electric Aircraft
SAE Technical Papers | 1993
|More-electric aircraft - system considerations
IET Digital Library Archive | 1999
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