System and method for flight control in electric aircraft

1. A system for flight control in electric aircraft, the system comprising:

a mixer, wherein the mixer includes circuitry configured to:

receive an 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; and

generate, as a function 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.

2. The system of claim 1 , wherein the system further comprises a flight controller, wherein the flight controller is configured to provide the initial vehicle torque signal comprising a plurality of attitude commands.

3. The system of claim 1 , wherein determining the plurality of modified attitude commands is further configured to include:

determining a modified pitch command as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data;

determining a modified roll command as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data;

determining a modified collective command as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data; and

determining a modified yaw command as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data.

4. The system of claim 1 , wherein the mixer comprises an inertia compensator.

5. The system of claim 1 , wherein the inertia compensator comprises a lead filter.

6. The system of claim 1 , wherein the mixer is implemented using an electrical logic circuit.

7. The system of claim 1 , wherein the mixer is implemented using a processor.

8. The system of claim 1 , wherein the mixer is further configured to generate, as a function of the output torque command, a remaining vehicle torque.

9. The system of claim 8 , wherein the mixer is further configured to determine a plurality of modified attitude commands as a function of the at least a vehicle torque limit, the plurality of attitude commands, the plurality of prioritization data, and the remaining vehicle torque.

10. The system of claim 8 , wherein the remaining vehicle torque comprises the remaining vehicle torque capability in an aircraft's pitch moment.

11. The system of claim 8 , wherein the remaining vehicle torque comprises the remaining vehicle torque capability in an aircraft's roll moment.

12. A method for flight control in electric aircraft, the method comprising:

receiving, at a mixer, an 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; and

generating, at the mixer, as a function 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.

13. The method of claim 12 , wherein the method further comprises providing, at the flight controller, the initial vehicle torque signal comprising at least an attitude command.

14. The method of claim 12 , wherein determining the plurality of modified attitude commands is further configured to include:

determining a modified pitch command as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data;

determining a modified roll command as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data;

determining a modified collective command as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data; and

determining a modified yaw command as a function of the at least a vehicle torque limit, the plurality of attitude commands, and the plurality of prioritization data.

15. The method of claim 12 , wherein the mixer comprises an inertia compensator.

16. The method of claim 12 , wherein the mixer is implemented using a processor.

17. The method of claim 12 , wherein the method further comprises generating, at the mixer, a remaining vehicle torque as a function of the output torque command.

18. The method of claim 17 , wherein the method further comprises determining a plurality of modified attitude commands as a function of the at least a vehicle torque limit, the plurality of attitude commands, the plurality of prioritization data, and the remaining vehicle torque.

19. The method of claim 17 , wherein the remaining vehicle torque comprises the remaining vehicle torque capability in an aircraft's yaw moment.

20. The method of claim 17 , wherein the remaining vehicle torque comprises the remaining vehicle torque capability in an aircraft's assisted lift.