System for establishing a primary function display in an electrical vertical takeoff and landing aircraft

1. A system for establishing a primary function display for an electrical vertical takeoff and landing (eVTOL) aircraft, the system comprising:

an electric aircraft, wherein the electric aircraft comprises:

an energy source, wherein the energy source is configured to power the electric aircraft; and

a cockpit, wherein the cockpit comprises a display configured to display at least a datum;

a plurality of sensors onboard the electric aircraft, the plurality of sensors configured to:

detect at least a metric, wherein the at least a metric includes a performance metric of the energy source of the electric aircraft;

a controller configured to:

receive the at least a metric;

generate the at least a datum based on the at least a metric, wherein the at least a datum includes a state of charge based on the performance metric; and

generate a visual output at the display based on the at least a datum, wherein the visual output includes the state of charge.

2. The system of claim 1 , wherein the electric aircraft further comprises at least one downward thrusting propulsor, wherein the at least one downward thrusting propulsor is configured to generate lift.

3. The system of claim 2 , wherein the electric aircraft further comprises at least one wing, wherein the at least one wing is configured to generate lift as a result of a forward airspeed of the electric aircraft.

4. The system of claim 1 , wherein the plurality of sensors further comprises a temperature sensor.

5. The system of claim 4 , wherein the at least a metric comprises a battery temperature.

6. The system of claim 1 , wherein:

the electric aircraft further comprises an electric propulsor powered by an electric motor;

the plurality of sensors are further configured to detect a torque datum as a function of the electric motor; and

the controller is further configured to:

receive the torque datum; and

generate another visual output at the display based on the torque datum, wherein the visual output includes the torque datum.

7. The system of claim 1 , wherein generating the at least a datum comprises determining a power-production capability of the energy source.

8. The system of claim 7 , wherein:

the energy source comprises a plurality of energy sources; and

determining a power-production capability of the energy source comprises determining a plurality of component energy capabilities for each of the plurality of energy sources.

9. The system of claim 8 , wherein the controller is further configured to determine a lowest component energy capability of the plurality of component energy capabilities.

10. The system of claim 7 , wherein determining a power-production capability of the energy source comprises determining a time remaining in rotor-based flight.

11. A method for a primary function display for an electrical vertical takeoff and landing (eVTOL) aircraft, the method comprising:

detecting, at a plurality of sensors located onboard an electric aircraft, at least a metric wherein the at least a metric includes a performance metric of an energy source of the electric aircraft;

receiving, at a controller, the at least a metric;

generating, at the controller, at least a datum based on the at least a metric, wherein the at least a datum includes a state of charge based on the performance metric; and

generating, at the controller, a visual output at a display based on the at least a datum, wherein the visual output includes the state of charge and the display is in a cockpit of the electric aircraft.

12. The method of claim 11 , wherein the electric aircraft comprises at least one downward thrusting propulsor, wherein the at least one downward thrusting propulsor is configured to generate lift.

13. The method of claim 12 , wherein the electric aircraft further comprises at least one wing, wherein the at least one wing is configured to generate lift as a result of a forward airspeed of the electric aircraft.

14. The method of claim 11 , wherein the plurality of sensors further comprises a temperature sensor.

15. The method of claim 11 , wherein the at least a metric comprises a battery temperature.

16. The method of claim 11 , further comprising:

powering, using an electric motor, an electric propulsor of the electric aircraft;

detecting, using the plurality of sensors, a torque datum as a function of the electric motor:

receiving, using the controller, the torque datum; and

generating, using the controller, another visual output at the display based on the torque datum, wherein the visual output includes the torque datum.

17. The method of claim 11 , wherein generating the at least a datum comprises determining a power-production capability of the energy source.

18. The method of claim 17 , wherein:

the energy source comprises a plurality of energy sources; and

determining a power-production capability of the energy source comprises determining a plurality of component energy capabilities for each of the plurality of energy sources.

19. The method of claim 18 , further comprising determining, at the controller, a lowest component energy capability of the plurality of component energy capabilities.

20. The method of claim 17 , wherein determining a power-production capability of the energy source comprises determining a time remaining in rotor-based flight.