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

1. A blended wing body aircraft with a fuel cell, the aircraft comprising:

a blended wing body aircraft;

at least a first fuel store located within a transitional portion of the blended wing body aircraft and configured to store a first fuel, wherein the at least a first fuel store comprises a fuel environment mitigation configured to regulate the temperature and pressure of the first fuel, wherein the fuel environment mitigation comprises an insulation, wherein the insulation comprises a vacuum chamber disposed between an inner wall of the at least a first fuel store and an outer wall of the at least a first fuel store, and a pressure vessel wherein the pressure vessel is further configured to control fuel pressure;

at least a fuel cell configured to combine the first fuel with oxygen to produce electricity;

at least a second fuel store located within the blended wing body aircraft and configured to store a second fuel wherein the at least a second fuel store comprises a second environment mitigation configured to regulate the temperature and pressure of the second fuel, wherein the second fuel environment mitigation comprises a second insulation, wherein the second insulation comprises a second vacuum chamber disposed between an inner wall of the at least a second fuel store and an outer wall of the at least a second fuel store, and a second pressure vessel wherein the second pressure vessel is further configured to control a second fuel pressure;

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, wherein the auxiliary power system is configured to power an anti-ice system and a braking system while in flight;

at least a propulsor mechanically affixed to an upper aft surface of the blended wing body aircraft and configured to propel the blended wing body aircraft; and

at least a nacelle configured to encapsulate the at least a propulsor.

2. The aircraft of claim 1 , wherein the first fuel comprises one or more of liquid hydrogen and natural gas.

3. The aircraft of claim 1 , wherein the second fuel comprises one or more of a kerosene based fuel and a gasoline based fuel.

4. The aircraft of claim 1 , 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.

5. The aircraft of claim 1 , wherein the at least a propulsor comprises at least an electric motor operatively connected with the at least a fuel cell, and wherein the at least a fuel cell is configured to power the at least an electric motor.

6. The aircraft of claim 1 , 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; and

at least an electric motor operatively connected with the at least a fuel cell; and wherein the at least a fuel cell is configured to power the at least an electric motor.

7. The aircraft of claim 1 , wherein the auxiliary power system is configured to power one or more of an avionic system, a flight control system, an environmental control system, a lighting system, a fuel system, a braking system, and a landing gear system.

8. The aircraft of claim 1 , wherein the at least a propulsor comprises a combustion engine and the auxiliary power system is further configured to start the internal combustion engine.

9. The aircraft of claim 1 , wherein the at least a second fuel store is located within a wing portion of the blended wing body.

10. A method of use of a blended wing body aircraft with a fuel cell, the method comprising:

storing a first fuel, using at least a first fuel store located within a transitional portion of a blended wing body of the blended wing body aircraft, wherein the at least a first fuel store comprises a fuel environment mitigation configured to regulate the temperature and pressure of the first fuel, wherein the fuel environment mitigation comprises an insulation, wherein the insulation comprises a vacuum chamber disposed between an inner wall of the at least a first fuel store and an outer wall of the at least a first fuel store, and a pressure vessel wherein the pressure vessel is further configured to control fuel pressure;

combining the first fuel with oxygen to produce electricity, using at least a fuel cell;

storing a second fuel, using at least a second fuel store located within the blended wing body, wherein the at least a second fuel store comprises a second environment mitigation configured to regulate the temperature of the second fuel, wherein the second fuel environment mitigation comprises a second insulation, wherein the second insulation comprises a second vacuum chamber disposed between an inner wall of the at least a second fuel store and an outer wall of the at least a second fuel store, and a second pressure vessel wherein the second pressure vessel is further configured to control a second fuel pressure;

powering, using the at least a fuel cell, an auxiliary power system operatively connected with the at least a fuel cell, wherein the auxiliary power system is configured to power an anti-ice system and a braking system while in flight; and

propelling the blended wing body aircraft, using at least a propulsor mechanically affixed to an upper aft surface the blended wing body aircraft, wherein the at least a propulsor is encapsulated by at least a nacelle.

11. The method of claim 10 , wherein the first fuel comprises one or more of liquid hydrogen and natural gas.

12. The method of claim 10 , wherein the second fuel comprises one or more of a kerosene based fuel and a gasoline based fuel.

13. The method of claim 10 , further comprising:

burning, using at least a combustion engine of the at least a propulsor, the second fuel; and

producing, using the at least a combustion engine, mechanical work which is used to power the at least a propulsor.

14. The method of claim 10 , further comprising:

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

15. The method of claim 10 , further comprising:

burning, using at least a combustion engine of the at least a propulsor, the second fuel;

producing, using the at least a combustion engine, mechanical work which is used to power the at least a propulsor; and

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

16. The method of claim 10 , further comprising:

powering, using the auxiliary power system, one or more of an avionic system, a flight control system, an environmental control system, a lighting system, a fuel system, a braking system, and a landing gear system.

17. The method of claim 10 , further comprising:

starting, using the auxiliary power unit, a combustion engine of the at least a propulsor.

18. The method of claim 10 , wherein the at least a second fuel store is located within a wing portion of the blended wing body.