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.


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    Titel :

    Power system for more electric aircraft


    Beteiligte:

    Erscheinungsdatum :

    23.05.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H01M Verfahren oder Mittel, z.B. Batterien, für die direkte Umwandlung von chemischer in elektrische Energie , PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY



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    Power System Characteristics for More Electric Aircraft

    Hansen, Irving G. | SAE Technical Papers | 1993


    More-electric aircraft - system considerations

    Moir, I. | IET Digital Library Archive | 1999