Method of operating a fuel cell assembly for an aircraft

1. A method of operating a fuel cell assembly for an aircraft, the method comprising:

receiving flight load predictor data for a scheduled flight of the aircraft prior to initiation of the scheduled flight of the aircraft; and

reconfiguring the fuel cell assembly in response to the received flight load predictor data prior to the initiation of the scheduled flight of the aircraft, wherein reconfiguring the fuel cell assembly comprises adding or removing a fuel cell module to or from the fuel cell assembly to increase or decrease a power capacity of the fuel cell assembly.

2. The method of claim 1 , wherein receiving flight load predictor data comprises receiving data indicative of a passenger load for the scheduled flight, weather data for the scheduled flight, historical data of the scheduled flight, or a combination thereof.

3. The method of claim 1 , wherein receiving flight load predictor data comprises receiving data indicative of a passenger load for the scheduled flight.

4. The method of claim 1 , wherein receiving flight load predictor data comprises receiving data indicative of an anticipated electrical load for the scheduled flight being higher than an electrical load for a flight preceding the scheduled flight, and wherein reconfiguring the fuel cell assembly comprises adding the fuel cell module to the fuel cell assembly to increase the power capacity of the fuel cell assembly.

5. The method of claim 4 , wherein adding the fuel cell module to the fuel cell assembly comprises fluidly connecting the fuel cell module to a fuel source of the fuel cell assembly and to an air source of the fuel cell assembly, and electrically connecting the fuel cell module to a power electronics device of the fuel cell assembly.

6. The method of claim 4 , wherein reconfiguring the fuel cell assembly comprises increasing the power capacity of the fuel cell assembly by at least 10% and up to 500%.

7. The method of claim 6 , wherein removing the fuel cell module from the fuel cell assembly comprises fluidly disconnecting the fuel cell module from a fuel source of the fuel cell assembly and from an air source of the fuel cell assembly, and electrically disconnecting the fuel cell module from a power electronics device of the fuel cell assembly.

8. The method of claim 6 , wherein the fuel cell assembly is positioned within the aircraft, and wherein removing the fuel cell module from the fuel cell assembly comprises removing the fuel cell module from the aircraft.

9. The method of claim 6 , wherein reconfiguring the fuel cell assembly comprises decreasing the power capacity of the fuel cell assembly by at least 10% and up to 75%.

10. The method of claim 1 , wherein receiving flight load predictor data comprises receiving data indicative of an anticipated electrical load for the scheduled flight being less than an electrical load for a flight preceding the scheduled flight, and wherein reconfiguring the fuel cell assembly comprises removing the fuel cell module from the fuel cell assembly to decrease the power capacity of the fuel cell assembly.

11. A power system for an aircraft, the aircraft comprising a fuselage, a wing, and a propulsor, the power system comprising:

a fuel cell assembly configured to be positioned within the fuselage, the wing, the propulsor, or a combination thereof when installed in the aircraft, the fuel cell assembly comprising:

a plurality of fuel cell modules including a first fuel cell module, the first fuel cell module independently removable from the fuel cell assembly relative to one or more other fuel cell modules of the plurality of fuel cell modules; and

a controller configured to receive flight load predictor data for a scheduled flight of the aircraft prior to initiation of the scheduled flight of the aircraft, the plurality of fuel cell modules being reconfigurable in response to the received flight load predictor data to increase or decrease a power capacity of the fuel cell assembly.

12. The power system of claim 11 , the fuel cell assembly further comprises:

a fuel source;

an air source; and

a power electronics device, wherein each of the plurality of fuel cell modules is fluidly coupled to the fuel source and the air source, and electrically coupled to the power electronics device.

13. The power system of claim 12 , wherein the first fuel cell module is fluidly coupled to the fuel source and the air source in parallel with the one or more other fuel cell modules of the plurality of fuel cell modules.

14. The power system of claim 12 , wherein the plurality of fuel cell modules comprises a first fuel cell module, wherein the first fuel cell module comprises a fuel inlet, wherein first fuel cell module is fluidly coupled to the fuel source through a connection assembly formed in part by the fuel inlet, wherein the connection assembly comprises a shut-off valve and a fluid connection.

15. The power system of claim 12 , wherein the plurality of fuel cell modules comprises a first fuel cell module, wherein the first fuel cell module comprises an air inlet, wherein first fuel cell module is fluidly coupled to the air source through a connection assembly formed in part by the air inlet, wherein the connection assembly comprises a shut-off valve and a fluid connection.

16. The power system of claim 12 , wherein the fuel source is a fuel source of the aircraft.

17. The power system of claim 11 , wherein the plurality of fuel cell modules comprises at least three fuel cell modules.

18. The power system of claim 11 , wherein each fuel cell module of the plurality of fuel cell modules is independently removable from the fuel cell assembly relative to the other fuel cell modules of the plurality of fuel cell modules.

19. The power system of claim 11 , wherein the fuel cell assembly defines a reduced power capacity when the first fuel cell module is removed from the fuel cell assembly.

20. The power system of claim 11 , wherein the fuel cell assembly is configured to be positioned within the fuselage of the aircraft.