Systems and methods for flight control for an electric aircraft
Systems and methods for flight control on an electric aircraft. The system includes a propulsor configured to generate lift to propel an electric aircraft, a pilot input mechanically coupled to the electric aircraft, a sensor communicatively connected to the pilot input, and a flight controller communicatively connected to the sensor. Sensor is configured to detect an input datum from the pilot input and convert the input datum into a command datum for the propulsor as a function of input mapping. Input mapping is determined as a function of the phase of flight.
1. A system, comprising:
a propulsor configured to propel an electric aircraft;
a pilot input communicatively connected to the electric aircraft;
a sensor communicatively connected to the pilot input, wherein the sensor is configured to:
detect an input datum as a function of the pilot input; and
transmit the input datum to a flight controller; and
the flight controller communicatively connected to the sensor, the flight controller configured to:
determine a command datum to control the propulsor as a function of the input datum and an input mapping; and
change the input mapping as a function of a phase of flight,
wherein the input mapping includes an attitude command attitude hold (ACAH) input mapping and a rate command attitude hold (RCAH) input mapping,
wherein the flight controller is configured to use the ACAH input mapping during a hover phase of flight and use the RCAH input mapping during a transition phase of flight, and
wherein the transition phase of flight comprises a transition between vertical flight and edgewise flight.
2. The system of claim 1 , wherein the pilot input includes an inceptor.
3. The system of claim 1 , wherein the flight controller is further configured to determine the input mapping based at least in part on a second input datum detected as a function of the pilot input.
4. The system of claim 1 , wherein the input mapping includes a plurality of rate commands.
5. The system of claim 1 , wherein the input mapping further includes a rate hold.
6. The system of claim 1 , wherein the flight controller uses a machine learning model trained with training data based at least in part on a previous input mapping from a previous flight to determine the input mapping.
7. The system of claim 1 , wherein the flight controller uses a servomechanism to control attitude of the electric aircraft.
8. The system of claim 7 , wherein the servomechanism includes a PID controller.
9. The system of claim 1 , wherein the propulsor comprises one or more rigid blades.
10. A method, comprising:
generating, by a propulsor, lift to propel an electric aircraft;
communicatively connecting a pilot input to the electric aircraft;
detecting, by a sensor, an input datum as a function of the pilot input;
transmitting, by the sensor, the input datum to a flight controller;
determining, by the flight controller, a command datum to control the propulsor as a function of the input datum and an input mapping; and
changing, by the flight controller, the input mapping as a function of a phase of flight,
wherein the input mapping includes an attitude command attitude hold (ACAH) input mapping and a rate command attitude hold (RCAH) input mapping,
wherein the flight controller is configured to use the ACAH input mapping during a hover phase of flight and use the RCAH input mapping during a transition phase of flight, and
wherein the transition phase of flight comprises a transition between vertical flight and edgewise flight.
11. The method of claim 10 , wherein the pilot input includes an inceptor.
12. The method of claim 10 , further comprising determining, by the flight controller, the input mapping based at least in part on a second input datum detected as a function of the pilot input.
13. The method of claim 10 , wherein the input mapping includes a plurality of rate commands.
14. The method of claim 10 , wherein the input mapping further includes a rate hold.
15. The method of claim 10 , wherein the flight controller uses a machine learning model trained with training data based at least in part on a previous input mapping from a previous flight to determine the input mapping.
16. The method of claim 10 , further comprising using, by the flight controller, a servomechanism to control attitude of the electric aircraft.
17. The method of claim 16 , wherein the servomechanism includes a PID controller.
18. The method of claim 10 , wherein the propulsor comprises one or more rigid blades.