Systems and methods for regulating charging of an electric aircraft

1. A system for regulating charging of an electric aircraft, the system comprising:

a charging connector, wherein the charging connector comprises:

a housing configured to mate with an electric aircraft port of an electric aircraft;

at least a conductor configured to conduct a current; and

at least a control signal conductor configured to conduct a control signal, wherein each of the at least a conductor and the at least a control signal conductor are configured to make a connection with a mating component on the electric aircraft port when the housing is mated with the electric aircraft port; and

a controller communicatively connected to the charging connector, wherein the controller is configured to:

receive a voltage datum, through the at least a control signal conductor, from the electric aircraft;

regulate a charging voltage, as a function of the voltage datum, through the at least a conductor, to the electric aircraft, wherein regulating the charging voltage further comprises:

charging at least a battery of the electric aircraft in a plurality of phases;

wherein in a first charging phase the at least a battery is charged at a first constant current; and

wherein in a second charging phase the at least a battery is charged at a constant voltage; and

wherein in a third charging phase the at least a battery is charged at a second constant current that differs from the first constant current; and

optimizing each of the plurality of phases based on data from one or more sensors communicatively connected to the controller as a function of the charging phases; and

control a coolant flow, as a function of a control signal received through the at least a control signal conductor, to the at least a battery.

2. The system of claim 1 , wherein the controller is a part of the charging connector.

3. The system of claim 2 , wherein the controller is located within the housing of the charging connector.

4. The system of claim 1 , wherein the controller is further configured to receive a state of charge datum, through the at least a control signal conductor, from the electric aircraft.

5. The system of claim 1 , wherein the at least a conductor comprises at least a direct current conductor.

6. The system of claim 1 , wherein the charging connector is further configured to receive an electrical flow from a power supply.

7. The system of claim 6 , wherein the system further comprises an alternating current to direct current converter configured to convert an alternating current from the power supply to a direct current.

8. The system of claim 1 , wherein the charging connector is configured for charging an electric vertical takeoff and landing (eVTOL) aircraft.

9. A method for regulating charging of an electric aircraft, the method comprising:

mating a housing of a charging connector with an electric aircraft port of an electric aircraft, wherein the charging connector further comprises:

at least a conductor configured to conduct a current; and

at least a control signal conductor configured to conduct a control signal;

wherein mating the housing of the charging connector with the electric aircraft port further comprises connecting each of the at least a conductor and the at least a control signal conductor with a mating component on the electric aircraft port;

receiving, by a controller communicatively connected to the charging connector, a voltage datum, through the at least a control signal conductor, from the electric aircraft;

regulating, by the controller, a charging voltage, as a function of the voltage datum, through the at least a conductor, to the electric aircraft, wherein regulating the charging voltage further comprises:

charging, by the charging connector, at least a battery of the electric aircraft in a plurality of phases, wherein charging the at least a battery further comprises:

charging, in a first charging phase, the at least a battery at a first constant current; and

charging, in a second charging phase, the at least a battery at a constant voltage; and

charging, in a third charging phase, the at least a battery at a second constant current that differs from the first constant current; and

optimizing, by the controller, each of the plurality of phases based on data from one or more sensors communicatively connected to the controller as a function of the charging phases; and

controlling a coolant flow, as a function of a control signal received through the at least a control signal conductor, to the at least a battery.

10. The method of claim 9 , wherein the controller is a part of the charging connector.

11. The method of claim 10 , wherein the controller is located within the housing of the charging connector.

12. The method of claim 9 , wherein the method further comprises receiving, by the controller, a state of charge datum, through the at least a control signal conductor, from the electric aircraft.

13. The method of claim 9 , wherein the at least a conductor comprises at least a direct current conductor.

14. The system of claim 1 , wherein the method further comprises receiving, by the charging connector, an electrical flow from a power supply.

15. The method of claim 14 , wherein the method further comprises converting, by an alternating current to direct current converter, an alternating current from the power supply to a direct current.

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

17. The system of claim 1 , wherein the charging connector further comprises a coolant interface to deliver coolant to the at least a battery during charging.

18. The method of claim 9 , wherein the charging connector further comprises a coolant interface to deliver coolant to the at least a battery during charging.