High voltage distribution systems and methods

1. A high voltage distribution system for an electric aircraft, the system comprising:

at least a power source mechanically connected to an electric aircraft, wherein the at least a power source is configured to supply power to the electric aircraft;

a flight component mechanically connected to the electric aircraft; and

a high voltage distribution component comprising:

a power source connection configured to electrically connect the at least a power source and the high voltage distribution component;

a flight component connection configured to electrically connect the flight component and the high voltage distribution component, wherein the flight component comprises a plurality of propulsors;

a controller, wherein the controller is configured to:

control power to the at least a power source from an electric charger via the battery connection; and

control electrical power to the flight component from the at least a power source via the flight component connection; and

a multibus, wherein a first bus of the multibus is configured to supply power from a first power source to a first propulsor of the plurality of propulsors, and wherein a second bus of the multibus is configured to supply power from a second power source to a second propulsor of the plurality of propulsors.

2. The system of claim 1 , wherein the high voltage distribution component comprises a recharging port, where the recharging port is configured to receive power from the charger.

3. The system of claim 1 , wherein the flight component connection is configured to communicatively connect to a load of the flight component.

4. The system of claim 1 , wherein the flight component comprises an electric motor configured to convert the electric power from the high voltage distribution component into a mechanical movement of flight component.

5. The system of claim 1 , wherein the flight component comprises an aerodynamic surface.

6. The system of claim 1 , wherein the power source comprises a pack monitoring unit (PMU) configured to communication a condition of the power source to the controller of the high voltage distribution component.

7. The system of claim 1 , wherein the high voltage distribution component includes a bus tie, wherein the bus tie is configured initiate a supply of power from the second power source to the first propulsor if the first power source malfunctions.

8. The system of claim 1 , wherein the electric aircraft comprises an electric vertical takeoff and landing (eVTOL) aircraft.

9. A method for high voltage distribution for an electric aircraft, the method comprising:

providing a high voltage distribution system, the high voltage distribution system comprising:

at least a power source mechanically connected to an electric aircraft, wherein the at least a power source is configured to supply power to the electric aircraft;

a flight component mechanically connected to the electric aircraft; and

a high voltage distribution component comprising:

a power source connection configured to electrically connect the at least a power source and the high voltage distribution component;

a flight component connection configured to electrically connect the flight component and the high voltage distribution component, wherein the flight component comprises a plurality of propulsors; a controller, wherein the controller is configured to:

control power to the at least a power source from an electric charger via the battery connection; and

control electrical power to the flight component from the at least a power source via the flight component connection; and

a multibus, wherein a first bus of the multibus is configured to supply power from a first power source to a first propulsor of the plurality of propulsors, and wherein a second bus of the multibus is configured to supply power from a second power source to a second propulsor of the plurality of propulsors;

determining, by a controller of a high voltage distribution component, a charging power input of a power source, wherein the power source is mechanically connected to an electrical aircraft;

supplying, by the high voltage distribution component, a charging power correlated to the charging power input to the power source from an electric charger via a power source connection between the high voltage distribution component and the power source;

determining, by the controller, an actuating power input of a flight component; and

supplying, by the high voltage distribution component, an actuating power correlated to the actuating power input to the flight component from the power source via a flight component connection between the high voltage distribution component and the flight component.

10. The method of claim 9 , wherein the high voltage distribution component comprises a recharging port, where the recharging port is configured to receive power from the charger.

11. The method of claim 9 , wherein the flight component comprises an electric motor configured to convert the electric power from the high voltage distribution component into a mechanical movement of the flight component.

12. The method of claim 9 , wherein the flight component comprises an aerodynamic surface.

13. The method of claim 9 , wherein the power source comprises a pack monitoring unit (PMU) configured to communication a condition of the power source to the controller of the high voltage distribution component.

14. The method of claim 9 , wherein:

the power source comprises a plurality of battery packs; and

the flight component comprises a plurality of propulsors.

15. The method of claim 9 , wherein the high voltage distribution component includes a bus tie configured to initiate supply of power from the second power source to the first propulsor if the first power source malfunctions.

16. The method of claim 9 , wherein the electric aircraft comprises an electric vertical takeoff and landing (eVTOL) aircraft.