Methods and systems for flight control configured for use in an electric aircraft
A system for flight control configured for use in an electric aircraft includes a sensor configured to capture an input datum. The system includes an inertial measurement unit (IMU) and configured to detect an aircraft angle and an aircraft angle rate. The system includes a flight controller including an outer loop controller configured to receive the input datum from the sensor, receive the aircraft angle from the IMU, and generate a rate setpoint as a function of the input datum. The system includes an inner loop controller configured to receive the aircraft angle rate, receive the rate setpoint from the outer loop controller, and generate a moment datum as a function of the rate setpoint. The system includes a mixer configured to receive the moment datum, perform a torque allocation as a function of the moment datum, and generate a motor command datum as a function of the torque allocation.
1. A system for flight control configured for use in an electric aircraft, the system comprising:
at least a sensor, the at least a sensor configured to capture at least an input datum from a pilot;
an inertial measurement unit, the inertial measurement unit configured to:
detect at least an aircraft angle; and
detect at least an aircraft angle rate;
a flight controller, the flight controller comprising:
an outer loop controller, the outer loop controller configured to:
receive the at least an input datum from the at least a sensor;
receive the at least an aircraft angle from the inertial measurement unit; and
generate a rate setpoint as a function of the at least an input datum;
an inner loop controller, the inner loop controller configured to:
receive the at least an aircraft angle rate;
receive the rate setpoint from the outer loop controller; and
generate a moment datum as a function of the rate setpoint; and
a mixer, the mixer configured to:
receive the moment datum;
map vehicle level control torques, received from the inner loop controller, to actuator output;
solve at least an optimization problem;
perform a torque allocation as a function of the moment datum and at least an optimization problem, the torque allocation comprising a first torque to a first propulsor and a second torque to a second propulsor; and
generate at least a motor command datum as a function of the torque allocation.
2. The system of claim 1 , wherein at least a sensor is mechanically and communicatively connected to a throttle.
3. The system of claim 1 , wherein at least a sensor is mechanically and communicatively connected to an inceptor stick.
4. The system of claim 1 , wherein at least a sensor is mechanically and communicatively connected to at least a foot pedal.
5. The system of claim 1 , wherein the flight controller further comprises a processor.
6. The system of claim 1 , wherein the mixer further comprises a logic circuit.
7. The system of claim 1 , wherein the mixer further comprises an inertia compensator.
8. The system of claim 1 , wherein the inner loop controller further comprises a lead-lag filter.
9. The system of claim 1 , wherein the inner loop controller further comprises an integrator.
10. The system of claim 1 , wherein the motor torque command is transmitted to a plurality of flight components.
11. A method of flight control configured for use in electric aircraft, the method comprising:
capturing, at an at least a sensor, an at least an input datum from a pilot;
detecting, at the inertial measurement unit, at least an aircraft angle;
detecting, at the inertial measurement unit, at least an aircraft angle rate;
receiving, at the outer loop controller, at least an input datum from the at least a sensor;
receiving, at the outer loop controller, the at least an aircraft angle from the inertial measurement unit;
generating, at the outer loop controller, a rate setpoint as a function of the at least an input datum;
receiving, at the inner loop controller, the at least an aircraft angle rate from the inertial measurement unit;
receiving, at the inner loop controller, the rate setpoint from the outer loop controller;
generating, at the inner loop controller, a moment datum as a function of the rate setpoint;
receiving, at a mixer, the moment datum;
mapping vehicle level control torques, received from the inner loop controller, to actuator output;
solving, at a mixer, at least an optimization problem;
performing, at the mixer, a torque allocation as a function of the moment datum and at least an optimization problem, the torque allocation comprising a first torque to a first propulsor and a second torque to a second propulsor; and
generating, at the mixer, at least a motor command datum as a function of the torque allocation.
12. The method of claim 11 , wherein at least a sensor is mechanically and communicatively connected to a throttle.
13. The method of claim 11 , wherein at least a sensor is mechanically and communicatively connected to an inceptor stick.
14. The method of claim 11 , wherein at least a sensor is mechanically and communicatively connected to at least a foot pedal.
15. The method of claim 11 , wherein the flight controller is implemented using a processor.
16. The method of claim 11 , wherein the mixer is implemented using an electrical logic circuit.
17. The method of claim 11 , wherein the mixer comprises an inertia compensator.
18. The method of claim 11 , wherein the inner loop controller comprises a lead-lag filter.
19. The method of claim 1 , wherein the inner loop controller comprises an integrator.
20. The method of claim 11 , wherein the motor torque command is transmitted to a plurality of flight components.