Systems and methods to control gain for an electric aircraft
Systems and methods to control gain of an electric aircraft are provided in this disclosure. The system may include gain scheduling to provide stability of the electric aircraft at various dynamic states of operation. The system may include a sensor to obtain measurement datum of an operating state. The system may further include a controller that adjusts a control gain of the electric aircraft as a function of the measurement datum. The gain control may be determined by a gain schedule generated by the controller.
1. A system to control gains for an electric aircraft, the system comprising:
a controller communicatively connected to a sensor, the controller configured to:
receive a measurement datum from the sensor, wherein the measurement datum comprises a lift throttle of the electric aircraft when the electric aircraft is in manually operated flight, wherein the measurement datum comprises an airspeed of the electric aircraft when the electric aircraft is in automatedly operated flight, wherein the electric aircraft comprises an electric vertical takeoff and landing (eVTOL) aircraft;
determine an operating point of the electric aircraft as a function of the measurement datum; and
generate a gain schedule for executing a landing flare by the eVTOL aircraft as a function of a machine-learning model;
adjust a control gain of the electric aircraft as a function of the gain schedule, wherein the gain schedule comprises:
a first operating range, wherein if an operating point is within a first operating range, then the control gain is configured to be adjusted linearly and directly scaled; and
a second operating range, wherein if an operating point is within the second operating range, then the control gain is configured to be adjusted based on a generated attitude command that pitches the electric aircraft upward by a predetermined angle, wherein the gain control comprises altering a position of one or more flight components of the eVTOL aircraft to pitch the eVTOL aircraft upward; and
obtain a remaining vehicle torque, wherein remaining vehicle torque comprises remaining vehicle torque capability in a pitch moment of the eVTOL aircraft.
2. The system of claim 1 , wherein:
the first operating range includes a nominal airspeed range required to generate lift of the electric aircraft; and
the second operating range includes a landing airspeed range used for preparation of touchdown of the electric aircraft.
3. The system of claim 1 , wherein the measurement datum further comprises a spin speed of a rotor blade of the eVTOL aircraft.
4. The system of claim 1 , wherein the measurement datum further comprises a pitch angle of a rotor of the eVTOL aircraft.
5. The system of claim 1 , wherein the sensor comprises an inertial measurement unit (IMU).
6. The system of claim 1 , wherein:
the flight component comprises a control surface; and
gain control schedule comprises at least altering a position of the control surface to adjust an orientation of the aircraft by a specific amount over certain duration of time.
7. The system of claim 1 , wherein the controller comprises an outer loop controller and an inner loop controller.
8. The system of claim 1 , wherein the aircraft command comprises a movement of a flight component of the electric aircraft to pitch the aircraft upward by the predetermined angle.
9. The system of claim 1 , wherein the electric aircraft is a drone.
10. A method to control gains for an electric aircraft, the method comprising:
receiving, by a controller communicatively connected to a sensor, a measurement datum from the sensor, wherein the measurement datum comprises a lift throttle of the electric aircraft when the electric aircraft is in manually operated flight, wherein the measurement datum comprises an airspeed of the electric aircraft when the electric aircraft is in automatedly operated flight, wherein the electric aircraft comprises an electric vertical takeoff and landing (eVTOL) aircraft;
determining, by the controller, an operating point of the electric aircraft as a function of the measurement datum; and
generating, by the controller, a gain schedule as a function of a machine-learning model;
adjusting, by the controller, a control gain of the electric aircraft as a function of the gain schedule, wherein the gain schedule comprises:
a first operating range, wherein if an operating point is within a first operating range then gain control may be adjusted linearly and directly scaled; and
a second operating range, wherein if an operating point is within the second operating range then gain control may be adjusted based on a generated attitude command that pitches the electric aircraft upward by a predetermined angle.
11. The method of claim 10 , wherein:
the first operating range includes a nominal airspeed range required to generate lift of the electric aircraft; and
the second operating range includes a landing airspeed range used for preparation of touchdown of the electric aircraft.
12. The method of claim 10 , wherein the sensor comprises an inertial measurement unit (IMU).
13. The method of claim 10 , wherein the controller comprises an outer loop controller and an inner loop controller.
14. The method of claim 10 , wherein the aircraft command comprises a movement of a flight component of the electric aircraft to pitch the aircraft upward by the predetermined angle.
15. The method of claim 10 , wherein the electric aircraft is a drone.
16. The method of claim 10 , wherein the measurement datum further comprises a spin speed of a rotor blade of the eVTOL aircraft.
17. The method of claim 10 , wherein the measurement datum further comprises a pitch angle of a rotor of the eVTOL aircraft.
18. The method of claim 10 , wherein:
the flight component comprises a control surface; and
gain control schedule comprises at least altering a position of the control surface to adjust an orientation of the aircraft by a specific amount over certain duration of time.