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 torque datum associated with at least a propulsor;
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;
a mixer configured to operate in a first mode in which the mixer 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, a torque priority command datum; and
transmit, 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.
2. The system of claim 1 , wherein torque datum comprises a loss of torque detection associated with the at least a propulsor.
3. The system of claim 1 , wherein the mixer further comprises an inertia compensator.
4. The system of claim 1 , wherein the observer is configured to compare the torque prediction datum and the torque datum at regular intervals.
5. The system of claim 1 , wherein the observer is configured to indicate that the torque prediction datum and the torque datum comparison is greater than a predetermined threshold.
6. The system of claim 1 , wherein the torque datum is detected utilizing a least squares method.
7. The system of claim 1 , wherein the residual datum is difference between the torque prediction datum and the torque datum.
8. 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.
9. The system of claim 8 , wherein detection of a loss of torque further comprises detection of the loss of torque at multiple time intervals.
10. A method for fault detection and control in an electric aircraft, the method comprising:
detecting, at an at least a sensor, a torque datum associated with at least a propulsor;
generating, at an observer, a torque prediction datum associated with the at least a propulsor;
comparing, at the observer, the torque prediction datum and the torque datum;
generating, at the observer, as a function of the comparison, a residual datum;
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 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.
11. The method of claim 10 , wherein torque datum comprises a loss of torque detection associated with the at least a propulsor.
12. The method of claim 10 , wherein the mixer further comprises an inertia compensator.
13. The method of claim 10 , wherein the observer is configured to compare the torque prediction datum and the torque datum at regular intervals.
14. The method of claim 10 , wherein the observer is configured to indicate that the torque prediction datum and the torque datum comparison is greater than a predetermined threshold.
15. The method of claim 10 , wherein the torque datum is detected utilizing a least squares method.
16. The method of claim 10 , wherein the residual datum is the difference between the torque prediction datum and the torque datum.
17. The method of claim 10 , 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.
18. The method of claim 17 , wherein detection of a loss of torque further comprises detection of the loss of torque at multiple time intervals.