Systems and methods for fault detection and control in an electric aircraft

1. A system for fault detection and control in an electric aircraft, the system comprising:

at least a sensor, wherein the at least a sensor configured to detect a sensed datum associated with at least a flight component, wherein the at least a flight component comprises a plurality of propulsors configured to propel the electric aircraft in a fluid medium; and

a flight controller, the flight controller configured to determine a failure state of a first plurality of propulsors of the plurality of propulsors as a function of the sensed datum, wherein the flight controller further comprises:

a mixer configured to switch from a first mode in which the mixer is configured to control the plurality of propulsors with a first control allocation to a second mode in which the mixer is configured to control a second plurality of propulsors of the plurality of propulsors with a second control allocation, wherein the mixer comprises a circuitry configured to:

generate, as a function of the failure state, a torque priority command datum;

transmit, to the second plurality of propulsors, the torque priority command datum configured to alter a trajectory of the electric aircraft by a change in pitch and yaw utilizing the second plurality of propulsors of the plurality propulsors; and

wherein the second control allocation has less attitude control in at least one axis than the first control allocation.

2. The system of claim 1 , wherein the flight component comprises a failed propulsor of the plurality of propulsors and the sensed datum is a function of the failed propulsor of the plurality of propulsors.

3. The system of claim 2 , wherein the sensed datum is a function of a first motor of a plurality of motors of the failed propulsor.

4. The system of claim 2 , wherein the sensed datum is a function of a first inverter of a plurality of inverters of the failed propulsor.

5. The system of claim 1 , wherein the flight component comprises a failed propulsor of the plurality of propulsors and the sensed datum is a function of at least a motor of the failed propulsor.

6. The system of claim 1 , wherein the flight component comprises a failed battery and the sensed datum is a function of the failed battery.

7. The system of claim 1 , wherein the second control allocation has no yaw control.

8. The system of claim 1 , wherein the torque priority command datum comprises a command to modulate torque to the at least a propulsor as a function of the failure state.

9. The system of claim 8 , wherein determination of the failure state further comprises detecting the sensed datum associated with the at least a flight component at multiple time intervals.

10. The system of claim 1 , further comprising:

a pilot control located within the electric aircraft and configured to generate a command as a function of a pilot input; and

wherein the mixer is further configured to:

receive the command from the pilot control; and

generate the torque priority command datum as a function of the command.

11. A method for fault detection and control in an electric aircraft, the method comprising:

detecting, at an at least a sensor, a sensed datum associated with at least a flight component, wherein the at least a flight component comprises a plurality of propulsors configured to propel the electric aircraft in a fluid medium;

determining, at a flight controller, as a function of the sensed datum, a failure state of a first plurality of propulsor of the plurality of propulsors;

generating, at a mixer that is configured to switch from a first mode in which the mixer is configured to control the plurality of propulsors with a first control allocation to a second mode in which the mixer is configured to control a second plurality of propulsor of the plurality propulsors with a second control allocation, as a function of the failure state, a torque priority command datum; and

transmitting, to the second plurality of propulsors, the torque priority command datum configured to alter a trajectory of the electric aircraft by a change in pitch and yaw utilizing the second plurality of propulsors of the plurality of propulsors; and

wherein the second control allocation has less attitude control in at least one axis than the first control allocation.

12. The method of claim 11 , wherein the flight component comprises a failed propulsor of the plurality of propulsors and the sensed datum is a function of the failed propulsor of the plurality of propulsors.

13. The method of claim 12 , wherein the sensed datum is a function of a first motor of a plurality of motors of the failed propulsor.

14. The method of claim 12 , wherein the sensed datum is a function of a first inverter of a plurality of inverters of the failed propulsor.

15. The method of claim 11 , wherein the flight component comprises a failed propulsor of the plurality of propulsors and the sensed datum is a function of at least a motor of the failed propulsor.

16. The method of claim 11 , wherein the flight component comprises a failed battery and the sensed datum is a function of the failed battery.

17. The method of claim 11 , wherein the second control allocation has no yaw control.

18. The method of claim 11 , wherein the torque priority command datum comprises a command to modulate torque to the at least a propulsor as a function of the failure state.

19. The method of claim 18 , wherein determination of the failure state further comprises detecting the sensed datum at multiple time intervals.

20. The method of claim 11 , further comprising:

generating, using a pilot control located within the electric aircraft, a command as function of a pilot input;

receiving, using the mixer, the command from the pilot control; and

generating, using the mixer, the torque priority command datum as a function of the command.