Systems and methods for redundant flight control in an aircraft

1. A system for redundant flight control configured for use in an aircraft, the system comprising:

a flight component attached to an aircraft, wherein a movement of the flight component is configured to adjust an attitude of the aircraft;

a plurality of actuators comprising a first actuator and a second actuator, wherein each of the first actuator and the second actuator is attached to the flight component and configured to move the flight component;

a pilot control communicatively connected to each actuator and configured to generate an attitude command to the plurality of actuators; and

at least a sensor communicatively connected to the pilot control and each actuator, wherein the at least a sensor is configured to:

detect a disablement of the first actuator, wherein the disablement comprises a loss of communicative connection between the first actuator and the pilot control;

generate a failure datum as a function of the loss of communicative connection between the first actuator and the pilot control; and

transmit the failure datum to the pilot control, wherein the second actuator is able to move the flight component if the first actuator is disabled.

2. The system of claim 1 , wherein the at least a sensor is configured to detect the attitude command from the pilot control.

3. The system of claim 1 , wherein the pilot control is configured to receive the failure datum from the at least a sensor and, subsequently, generate the attitude command to the second actuator to move the flight component.

4. The system of claim 1 , wherein the pilot control comprises a processor configured to receive the failure datum from the at least a sensor.

5. The system of claim 1 , wherein the pilot control comprises a pilot interfacing component.

6. The system of claim 5 , wherein the pilot interfacing component comprises an inceptor, collective, foot brake, throttle lever, or control wheel.

7. The system of claim 1 , wherein flight component comprises an aerodynamic surface.

8. The system of claim 7 , wherein the flight component comprises an aileron, an edge slat, an elevator, a rudder, balance and anti-balance tabs, flaps, spoilers, a trim, or a mass balance.

9. The system of claim 1 , wherein the aircraft further comprises an electric aircraft.

10. The system of claim 1 , wherein at least one of the plurality of actuators is enclosed in outer-mold-lines (OML) of the aircraft.

11. The system of claim 1 , wherein at least a portion of at least one of the plurality of actuators protrudes through outer-mold-lines (OML) of the aircraft.

12. The system of claim 11 , where the protruding portion of the at least one plurality of actuators is oriented relative to the OML so as to minimize drag.

13. The system of claim 1 , wherein:

the attitude command comprises an electrical signal; and

the first actuator and the second actuator each comprise a conversion mechanism configured to convert the electrical signal to a mechanical movement of the flight component.

14. The system of claim 13 , where the conversion mechanism is an electrical motor.

15. A method of redundant flight control in an aircraft, the method comprising:

generating, by a pilot control, an attitude command;

receiving, by the plurality of actuators, the attitude command, wherein the plurality of actuators comprises:

a first actuator and;

a second actuator able to move the flight component if the first actuator is disabled;

moving, by the plurality of actuators, the flight component;

detecting, by at least a sensor, a disablement of the first actuator, wherein the disablement comprises a loss of communicative connection between the first actuator and the pilot control;

generating, by the at least a sensor, a failure datum as a function of the loss of communicative connection between the first actuator and the pilot control; and

transmitting, by the at least a sensor, the failure datum to the pilot control.

16. The method of claim 15 , wherein generating an attitude command further comprises:

detecting, by the at least a sensor, the attitude command of the pilot control;

receiving, by the pilot control, the failure datum from the at least a sensor;

generating, by the pilot control, a secondary attitude command to the second actuator; and

moving, by the second actuator, the flight component in response to the secondary attitude command.

17. The method of claim 15 , wherein:

the attitude command comprises an electrical signal that is converted by the plurality of actuators to a mechanical signal; and

the first actuator and the second actuator each comprise a conversion mechanism for converting the electrical signal to a mechanical signal.

18. The method of claim 15 , wherein the flight component comprises an aerodynamic surface.

19. The method of claim 15 , wherein the pilot control comprises a pilot interfacing component.

20. The method of claim 15 , wherein the aircraft comprises an electric aircraft.