Blended wing body aircraft with a combustion engine and method of use

1. A system for a blended wing body aircraft with a combustion engine, the aircraft comprising:

a blended wing body;

at least a fuel source located within the blended wing body and configured to store a fuel, wherein the fuel includes liquid hydrogen, wherein the fuel source comprises:

a multi-bubble fuel tank comprising at least a plurality of main lobes and at least four small lobes positioned on an outer perimeter of the plurality of main lobes, wherein each small lobe defines a varying volume from each remaining small lobes of the at least four small lobes, and wherein each junction of the multi-bubble tank comprises a continuous septum that partitions the multi-bubble tank into compartments and prevents fluid communication therethrough between the compartments;

an inner wall and an outer wall with a vacuum chamber disposed between the inner wall and the outer wall, wherein the outer wall comprises a reflective material; and

at least a propulsor configured to propel the blended wing body aircraft, the at least a propulsor comprising a combustion engine configured to:

burn the fuel from the fuel source; and

produce mechanical work to power the at least a propulsor.

2. The system of claim 1 , wherein the at least a fuel source comprises at least a fuel environment control mitigation.

3. The system of claim 1 , wherein the at least a fuel source is pressurized.

4. The system of claim 1 , further comprising at least an auxiliary power unit powered by the fuel and mechanically affixed to the aircraft.

5. The system of claim 1 , further comprising at least a fuel cell powered by the fuel.

6. The system of claim 5 , wherein the at least a fuel cell is configured to power at least an electric motor.

7. The system of claim 5 , wherein the at least a fuel cell comprises an oxygen source.

8. The system of claim 5 , wherein the at least a fuel cell is configured to provide electrical power to aircraft systems.

9. The system of claim 5 , wherein the at least a fuel cell is configured to power one or more of an avionic system, a flight control system, an environmental control system, an anti-ice system, a lighting system, a fuel system, a braking system, and a landing gear system.

10. The system of claim 5 , wherein the at least a fuel cell is configured to start the combustion engine.

11. A method of use of a system for a blended wing body aircraft with a combustion engine, the method comprising:

storing a fuel using at least a fuel source located within a blended wing body of the blended wing body aircraft, wherein the fuel source comprises:

a multi-bubble fuel tank comprising at least a plurality of main lobes and at least four small lobes positioned on an outer perimeter of the plurality of main lobes, wherein each small lobe defines a varying volume from each remaining small lobes of the at least four small lobes, and wherein each junction of the multi-bubble tank comprises a continuous septum that partitions the multi-bubble tank into compartments and prevents fluid communication therethrough between the compartments; and

an inner wall and an outer wall with a vacuum chamber disposed between the inner wall and the outer wall, wherein the outer wall comprises a reflective material;

propelling the aircraft, using at least a propulsor mechanically affixed to the blended wing body aircraft, the at least at propulsor comprising a combustion engine;

burning, at the combustion engine, the fuel from the fuel source; and

producing, at the combustion engine, mechanical work to power the at least a propulsor.

12. The method of claim 11 , wherein the at least a fuel source comprises at least a fuel environment control mitigation.

13. The method of claim 11 , wherein the at least a fuel source is pressurized.

14. The method of claim 11 , further comprising at least an auxiliary power unit powered by the fuel and mechanically affixed to the aircraft.

15. The method of claim 11 , further comprising at least a fuel cell powered by the fuel.

16. The method of claim 15 , wherein the at least a fuel cell is configured to power at least an electric motor.

17. The method of claim 15 , wherein the at least a fuel cell comprises an oxygen source.

18. The method of claim 15 , wherein the at least a fuel cell is configured to provide electrical power to aircraft systems.

19. The method of claim 15 , wherein the at least a fuel cell is configured to power one or more of an avionic system, a flight control system, an environmental control system, an anti-ice system, a lighting system, a fuel system, a braking system, and a landing gear system.

20. The method of claim 15 , wherein the at least a fuel cell is configured to start the combustion engine.