Blended wing body aircraft with a fuel cell and method of use

1 . An aircraft with a fuel cell, the aircraft comprising:

at least a first fuel store located within the aircraft and configured to store a first fuel, wherein the first fuel of the at least a first fuel store is consumed during a first flight mode of the aircraft;

at least a fuel cell operatively connected to an auxiliary power unit and configured to combine the first fuel with oxygen to produce electricity for the auxiliary power unit during the first flight mode of the aircraft;

at least a second fuel store located within the aircraft and configured to store a second fuel, wherein the second fuel of the at least a second fuel store is consumed solely during a second flight mode of the aircraft, wherein the first fuel is consumed first and the second fuel is consumed second; and

at least a flight component mechanically affixed to the aircraft and configured to propel the aircraft.

2 . The aircraft of claim 1 , further comprising:

a blended wing body, wherein the at least a first fuel store is located within a transitional portion area of the blended wing body and the at least a second fuel store is located within a wing portion of the blended wing body.

3 . The aircraft of claim 1 , further comprising:

a computing device, wherein the computing device is configured to generate a flight command as a function of sensor data, wherein the flight command is configured to control the at least a flight component to perform the first flight mode and the second flight mode.

4 . The aircraft of claim 3 , wherein the computing device is further configured to control which of the at least a first fuel store and the at least a second fuel store is drawn from as a function of the first flight mode and the second flight mode.

5 . The aircraft of claim 3 , wherein the computing device is further configured to generate the flight command as a function of a pilot input.

6 . The aircraft of claim 1 , wherein the at least a flight component comprises at least a propulsor, wherein the at least a propulsor comprises at least a combustion engine that burns the second fuel and produces mechanical work which is used to power the at least a propulsor.

7 . The aircraft of claim 6 , wherein the at least a propulsor comprises at least an electric motor operatively connected with the at least a fuel cell, wherein the at least a fuel cell is configured to power the at least an electric motor.

8 . The aircraft of claim 1 , wherein the at least a flight component comprises an auxiliary power system operatively connected with the at least a fuel cell, wherein the at least a fuel cell is configured to power the auxiliary power system.

9 . The aircraft of claim 1 , wherein:

the first flight mode comprises a first portion of a flight time of the aircraft; and the second flight mode comprises a second portion of a flight time of the aircraft.

10 . The aircraft of claim 1 , wherein:

the first flight mode comprises a takeoff and landing of the aircraft; and the second flight mode comprises a cruising of the aircraft.

11 . A method of use of an aircraft with a fuel cell, the method comprising:

storing, using at least a first fuel store located within the aircraft, a first fuel;

combining, using at least a fuel cell operatively connected to an auxiliary power unit, the first fuel with oxygen to produce electricity for the auxiliary power unit during a first flight mode of the aircraft;

storing, using at least a second fuel store located within the aircraft, a second fuel, wherein the first fuel is consumed first and the second fuel is consumed second;

propelling, using at least a flight component mechanically affixed to the aircraft, the aircraft;

consuming the first fuel of the at least a first fuel store during a first flight mode of the aircraft; and

consuming the second fuel of the at least a second fuel store solely during a second flight mode of the aircraft.

12 . The method of claim 11 , further comprising:

locating the at least a first fuel store within a transitional portion area of a blended wing body of the aircraft and the at least a second fuel store within a wing portion of the blended wing body of the aircraft.

13 . The method of claim 11 , further comprising:

generating, using a computing device of the aircraft, a flight command as a function of sensor data, wherein the flight command is configured to control the at least a flight component to perform the first flight mode and the second flight mode.

14 . The method of claim 13 , further comprising:

controlling, using the computing device of the aircraft, which of the at least a first fuel store and the at least a second fuel store is drawn from as a function of the first flight mode and the second flight mode.

15 . The method of claim 13 , further comprising:

generating, using the computing device of the aircraft, the flight command as a function of a pilot input.

16 . The method of claim 11 , wherein the at least a flight component comprises at least a propulsor, wherein the at least a propulsor comprises at least a combustion engine that burns the second fuel and produces mechanical work which is used to power the at least a propulsor.

17 . The method of claim 16 , further comprising:

powering, using the at least a fuel cell, at least an electric motor of the at least a propulsor, wherein the at least an electric motor is operatively connected with the at least a fuel cell.

18 . The method of claim 11 , further comprising:

powering, using the at least a fuel cell, an auxiliary power system of the at least a flight component, wherein the auxiliary power system is operatively connected with the at least a fuel cell.

19 . The method of claim 11 , wherein:

the first flight mode comprises a first portion of a flight time of the aircraft; and

the second flight mode comprises a second portion of a flight time of the aircraft.

20 . The method of claim 11 , wherein:

the first flight mode comprises a takeoff and landing of the aircraft; and

the second flight mode comprises a cruising of the aircraft.