System and method for flight control in electric aircraft
A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive prioritization data including a prioritization datum corresponding to each of the plurality of attitude command, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the prioritization data, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.
1. A system for flight control in electric aircraft, the system comprising:
a flight controller, wherein the flight controller is configured to provide an initial vehicle torque signal comprising a plurality of attitude commands;
a mixer, wherein the mixer includes circuitry configured to:
receive the initial vehicle torque signal;
receive at least a vehicle torque limit;
receive a plurality of prioritization data, the plurality of prioritization data including a prioritization datum corresponding to each of the plurality of attitude commands;
determine a plurality of modified attitude commands as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data;
generate, as a function of the plurality of modified attitude commands, an output torque command, wherein the output torque command includes the initial vehicle torque signal adjusted as a function of the at least a vehicle torque limit; and
generate, as a function of the output torque command, a remaining vehicle torque.
2. The system of claim 1 , wherein the mixer comprises an inertia compensator.
3. The system of claim 2 , wherein the inertia compensator comprises a lead filter.
4. The system of claim 1 , wherein the mixer is implemented using an electrical logic circuit.
5. The system of claim 1 , wherein the mixer is implemented using a processor.
6. The system of claim 1 , wherein the flight controller is a proportional-integral-derivative (PID) controller.
7. The system of claim 1 , wherein the flight controller is configured to provide the initial vehicle torque signal as a function of a control algorithm.
8. The system of claim 1 wherein the flight controller is configured to provide the initial vehicle torque signal as a function of an autonomous function.
9. The system of claim 1 , wherein the remaining vehicle torque comprises the remaining vehicle torque capability in an aircraft's pitch moment.
10. The system of claim 1 , wherein the remaining vehicle torque comprises the remaining vehicle torque capability in an aircraft's roll moment.
11. A method for flight control in electric aircraft, the method comprising:
providing, at a flight controller, an initial vehicle torque signal comprising at least an attitude command;
receiving, at a mixer, the initial vehicle torque signal including a plurality of attitude commands;
receiving, at the mixer, at least a vehicle torque limit;
receiving, at the mixer, a plurality of prioritization data including a prioritization datum corresponding to each of the plurality of attitude commands;
determining, at the mixer, a plurality of modified attitude commands as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data;
generating, at the mixer, as a function of the plurality of modified attitude commands, an output torque command, wherein the output torque command includes the initial vehicle torque signal adjusted as a function of the at least a vehicle torque limit; and
generating, at the mixer, as a function of the output torque command, a remaining vehicle torque.
12. The method of claim 11 , wherein the mixer comprises an inertia compensator.
13. The method of claim 12 , wherein the inertia compensator comprises a lead filter.
14. The method of claim 11 , wherein the mixer is implemented using an electrical logic circuit.
15. The method of claim 11 , wherein the mixer is implemented using a processor.
16. The method of claim 11 , wherein the flight controller is a proportional-integral-derivative (PID) controller.
17. The method of claim 11 , wherein providing the initial vehicle torque signal further comprises:
providing, using the flight controller, the initial vehicle torque signal as a function of a control algorithm.
18. The method of claim 11 , wherein providing the initial vehicle torque signal further comprises:
providing, using the flight controller, the initial vehicle torque signal as a function of an autonomous function.
19. The method of claim 11 , wherein the remaining vehicle torque comprises the remaining vehicle torque capability in an aircraft's yaw moment.
20. The method of claim 11 , wherein the remaining vehicle torque comprises the remaining vehicle torque capability in an aircraft's assisted lift.