System and method for distributed pilot control of an aircraft

1. A system for distributed pilot control of an aircraft, the system comprising:

a plurality of flight components;

an aircraft control located within the aircraft; and

an aircraft component attached to a flight component of the plurality of flight components, wherein the aircraft component is configured to:

receive, from a command sensor attached to the aircraft control, an aircraft command;

obtain, from an attitude sensor, an aircraft orientation; and

receive, as a function of a notification unit, a pilot signal; and

command the flight component to produce a response command as a function of the pilot signal, wherein producing the response command further comprises:

determining at least an aircraft response, wherein determining at least an aircraft response further comprises:

simulating an aircraft command adjustment as a function of a control algorithm; and

determining the aircraft response using the aircraft command adjustment; and

producing the response command as a function of the aircraft response.

2. The system of claim 1 , wherein the aircraft component is further configured to:

receive an alternate signal from an alternate aircraft component; and

command the flight component as a function of the alternate signal.

3. The system of claim 1 , wherein the aircraft control is configured to translate a desired command.

4. The system of claim 3 , wherein the desired command includes a desired torque for the flight component of the plurality of flight components.

5. The system of claim 1 , wherein the plurality of flight components includes a propulsor.

6. The system of claim 5 , wherein the propulsor includes a puller component.

7. The system of claim 5 , wherein the propulsor includes a pusher component.

8. The system of claim 1 , wherein the command sensor is configured to:

detect an aircraft command, wherein the aircraft command includes a desired output of the flight component of the plurality of flight components; and

transmit the aircraft command to the aircraft component.

9. The system of claim 8 , wherein transmitting the aircraft command further comprises converting the aircraft command to a digital electrical signal.

10. The system of claim 1 , wherein the attitude sensor is configured to:

detect an aircraft orientation, wherein the aircraft orientation includes an aircraft attitude; and

transmit the aircraft orientation to the aircraft component.

11. The system of claim 1 , wherein the aircraft component includes a microprocessor.

12. The system of claim 1 , wherein the response command includes an actuator command.

13. The system of claim 1 , wherein the response command includes a thrust command.

14. The system of claim 1 , wherein the control algorithm is configured to:

receive a segmented control algorithm;

determine a segmentation boundary as a function of the segmented control algorithm; and

create an optimized signal communication as a function of the segmentation boundary.

15. The system of claim 14 , wherein creating the optimized signal communication further comprises separating a plurality of signal codes across a communication network.

16. The system of claim 15 , wherein the communication network includes a master bus controller configured to synchronize timing of the plurality of signal codes.

17. The system of claim 1 , wherein simulating the aircraft command adjustment further comprises detecting a failure event and simulating the aircraft command adjustment as a function of the failure event.

18. The system of claim 1 , wherein determining the at least an aircraft response further comprises:

receiving, from the command sensor attached to the aircraft control, a first aircraft command;

obtaining, from a related flight component of the plurality of flight components, an adjustment impact; and

determining the at least an aircraft response as a function of the first aircraft command and the adjustment impact.