Aircraft having a controllable center of gravity and method of use

1. An aircraft having a controllable center of gravity, the aircraft comprising:

a blended wing body, wherein the blended wing body has no clear demarcation between a main body of the blended wing body and wings of the blended wing body at a leading edge of the wings of the blended wing body;

a first tank located within the blended wing body and configured to store a first portion of a ballast, wherein the ballast comprises a slurry;

a second tank configured to store a second portion of the ballast, located within the blended wing body and disposed substantially aft of the first tank;

at least a pipe configured to provide fluidic communication between the first tank and the second tank;

at least a pump configured to pump the ballast bidirectionally between the first tank and the second tank by way of the at least a pipe; and

a controller in communication with the at least a pump and configured to control a longitudinal ballast ratio of the first portion of the ballast relative the second portion of the ballast and affect an aircraft center of gravity.

2. The aircraft of claim 1 , wherein the slurry comprises solid particles denser than a constituent fluid.

3. The aircraft of claim 1 , wherein the controller is further configured to:

receive pump data through a sensor of the at least a pump, wherein the sensor is in electronic communication with the controller; and

send a pump command to the at least a pump based on the pump data.

4. The aircraft of claim 1 , further comprising:

at least a sensor in communication with the controller, wherein the at least a sensor is configured to:

detect a center of gravity phenomenon associated with one or more of the aircraft center of gravity and the ballast center of gravity; and

locate a gravity range of the aircraft center of gravity and the ballast center of gravity, wherein locating the gravity range includes controlling the ballast ratio.

5. The aircraft of claim 1 , wherein the ballast center of gravity affects the aircraft center of gravity by relocating the aircraft center of gravity to a favorable location within a permissible range.

6. The aircraft of claim 1 , further comprising a third tank configured to store a third portion of the ballast, located within the blended wing body and disposed substantially outboard of the first tank;

wherein the at least a pipe is further configured to provide fluid communication between the first tank and the third tank;

wherein the at least a pump is further configured to pump the ballast bidirectionally between the first tank and the third tank by way of the at least a pump; and

wherein the controller is further configured to control a lateral ballast ratio of the first portion of the ballast relative the third portion of the ballast and affect the aircraft center of gravity.

7. The aircraft of claim 6 , further comprising a fuel store, wherein the fuel store is configured to store liquid hydrogen fuel.

8. The aircraft of claim 1 , wherein the controller is further configured to control the ballast ratio as a function of inflight changes to the aircraft center of gravity.

9. The aircraft of claim 8 , wherein the inflight changes to the aircraft center of gravity result from consumption of fuel.

10. A method of controlling a center of gravity of an aircraft, the method comprising:

storing, using a first tank located within a blended wing body of the aircraft, a first portion of a ballast, wherein the blended wing body has no clear demarcation between a main body of the blended wing body and wings of the blended wing body at a leading edge of the wings of the blended wing body, wherein the ballast comprises a slurry;

storing, using a second tank located within the blended wing body and disposed substantially aft of the first tank, a second portion of the ballast;

providing, using at least a pipe, fluidic communication between the first tank and the second tank;

pumping, using at least a pump, the ballast bidirectionally between the first tank and the second tank by way of the at least a pipe; and

controlling, using a controller in communication with the at least a pump, a longitudinal ballast ratio of the first portion of the ballast relative the second portion of the ballast and affect an aircraft center of gravity.

11. The method of claim 10 , wherein the slurry comprises solid particles denser than a constituent fluid.

12. The method of claim 10 , wherein the controller is further configured to:

receive pump data through a sensor of the at least a pump, wherein the sensor is in electronic communication with the controller; and

send a pump command to the at least a pump based on the pump data.

13. The method of claim 10 , further comprising:

detecting, using at least a sensor in communication with the controller, a center of gravity phenomenon associated with one or more of the aircraft center of gravity and the ballast center of gravity; and

locating a gravity range of the aircraft center of gravity and the ballast center of gravity, wherein locating the gravity range includes controlling the ballast ratio.

14. The method of claim 10 , wherein the ballast center of gravity affects the aircraft center of gravity by relocating the aircraft center of gravity to a favorable location within a permissible range.

15. The method of claim 10 , further comprising:

storing, using a third tank located within the blended wing body and disposed substantially outboard of the first tank, a third portion of the ballast;

providing, using the at least a pipe, fluidic communication between the first tank and the third tank;

pumping, using the at least a pump, the ballast bidirectionally between the first tank and the third tank by way of the at least a pipe; and

controlling, using the controller, a lateral ballast ratio of the first portion of the ballast relative the third portion of the ballast and affect the aircraft center of gravity.

16. The method of claim 15 , further comprising storing, using a fuel store, liquid hydrogen fuel.

17. The method of claim 10 , wherein controlling the ballast ratio is performed as a function of inflight changes to the aircraft center of gravity.

18. The method of claim 17 , wherein the inflight changes to the aircraft center of gravity result from consumption of fuel.