Systems and methods for fault detection and control in an electric aircraft
A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.
1. A system for fault detection and control in an electric aircraft, the system comprising:
a flight controller, the flight controller comprising:
at least a sensor, wherein the at least a sensor configured to detect a sensed datum associated with at least a propulsor;
an observer, the observer configured to:
generate a prediction datum associated with the at least a propulsor;
compare the prediction datum with the sensed datum;
generate a residual datum as a function of the comparison; and
determine a failure state of the at least a propulsor as a function of the residual datum;
a mixer configured to operate in a first mode in which the mixer is configured to control a first plurality of the at least a propulsor and a second mode in which the mixer is configured to control a second plurality of the at least a propulsor, the mixer comprising circuitry configured to:
generate, as a function of the residual datum and the failure state, a torque priority command datum; and
transmit, to the at least a propulsor, the torque priority command datum configured to command operation of the first plurality of the at least a propulsor.
2. The system of claim 1 , wherein sensed datum comprises a speed of the at least a propulsor.
3. The system of claim 2 , wherein the observer is further configured to calculate a torque datum as a function of the sensed datum.
4. The system of claim 3 , wherein:
the prediction datum is a torque prediction datum; and
comparing the prediction datum with the sensed datum comprises comparing the torque prediction datum to the torque datum.
5. The system of claim 1 , wherein the mixer further comprises an inertia compensator.
6. The system of claim 1 , wherein the observer is configured to compare the prediction datum and the sensed datum at regular intervals.
7. The system of claim 1 , wherein the observer is configured to indicate that the prediction datum and the sensed datum comparison is greater than a predetermined threshold.
8. The system of claim 1 , wherein the residual datum is difference between the prediction datum and the sensed datum.
9. The system of claim 1 , wherein the torque priority command datum comprises a command to increase torque to the at least a propulsor as a function of the detection of a loss of torque.
10. The system of claim 9 , wherein detection of a loss of torque further comprises detection of the loss of torque at multiple time intervals.
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 propulsor;
generating, at an observer, a prediction datum associated with the at least a propulsor;
comparing, at the observer, the prediction datum and the sensed datum;
generating, at the observer, as a function of the comparison, a residual datum;
generating, at the observer, as a function of the residual datum, a failure state of the at least a propulsor;
generating, at a mixer that is configured to operate in a first mode in which the mixer is configured to control a first plurality of the at least a propulsor and a second mode in which the mixer is configured to control a second plurality of the at least a propulsor, as a function of the residual datum and the failure state, a torque priority command datum; and
transmitting, to the at least a propulsor, the torque priority command datum configured to command operation of at least one flight component of the electric aircraft.
12. The method of claim 11 , wherein sensed datum comprises a speed of the at least a propulsor.
13. The method of claim 12 , further comprising, calculating, at the observer, a torque datum as a function of the sensed datum.
14. The method of claim 13 , wherein:
the prediction datum is a torque prediction datum; and
comparing the prediction datum with the sensed datum comprises comparing the torque prediction datum to the torque datum.
15. The method of claim 11 , wherein the mixer further comprises an inertia compensator.
16. The method of claim 11 , wherein comparing the prediction datum and the sensed datum comprises comparing the prediction datum and the sensed datum at regular intervals.
17. The method of claim 11 , further comprising indicating, at the observer, that the prediction datum and the sensed datum comparison is greater than a predetermined threshold.
18. The method of claim 11 , wherein the residual datum is difference between the prediction datum and the sensed datum.
19. The method of claim 11 , wherein the torque priority command datum comprises a command to increase torque to the at least a propulsor as a function of the detection of a loss of torque.
20. The method of claim 19 , wherein detection of a loss of torque further comprises detection of the loss of torque at multiple time intervals.