Methods and systems for a distributed control system with supplemental attitude adjustment

1. A distributed control system with supplemental attitude adjustment, the system comprising:

an aircraft control, the aircraft control located within an aircraft having an aircraft attitude;

a plurality of flight components;

a plurality of aircraft components communicatively connected to the plurality of flight components, wherein each aircraft component of the plurality of aircraft components is configured to:

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

generate a response command directing the flight components as a function of an aggregate attitude, wherein the aggregate attitude combines a supplemental attitude with the aircraft attitude.

2. The system of claim 1 , further comprising an aircraft control component, the aircraft control component communicatively connected to the aircraft control, the aircraft control component configured to:

calculate the displacement of the aircraft control from a default position;

compare the displacement of the aircraft control against a first threshold; and

transmit an engagement datum to the command sensor indicating that the aircraft control is engaged if the displacement of the aircraft control exceeds the first threshold.

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

compare the displacement of the aircraft control against a second threshold, wherein the second threshold is less than the first threshold; and

transmit an engagement datum to the command sensor indicating that the aircraft control is disengaged if the displacement of the aircraft control does not exceed the second threshold.

4. The system of claim 1 , wherein each aircraft component of the plurality of aircraft components is configured to generate the supplemental attitude as a function of an engagement datum.

5. The system of claim 4 , wherein generating the supplemental attitude further comprises:

determining that the aircraft control is disengaged; and

choosing a position supplemental attitude as a function of the determination.

6. The system of claim 4 , wherein generating the supplemental attitude further comprises:

determining that the aircraft control is engaged; and

choosing a velocity supplemental attitude as a function of the determination.

7. The system of claim 6 , wherein each of the plurality of aircraft components is further configured to determine the velocity supplemental attitude by:

receiving a desired velocity, the desired velocity including a desired direction of movement;

receiving an actual velocity from a velocity sensor; and

generating a velocity supplemental attitude, comprising:

calculating the difference between the desired velocity and the actual velocity; and

calculating the part of the difference that is perpendicular to the desired direction of movement.

8. The system of claim 1 , wherein the plurality of aircraft components comprises a first aircraft component and a second aircraft component, the first aircraft component is further configured to:

receive an alternate signal from the second aircraft component; and

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

9. The system of claim 8 , wherein the first aircraft component is further configured to transmit an outgoing signal to the second aircraft component, wherein the outgoing signal contains the aggregate attitude.

10. The system of claim 1 , wherein each aircraft component of the plurality of aircraft components is configured to direct a flight component of a plurality of flight components to produce a response command based on the aggregate attitude, wherein the flight component of the plurality of flight components is attached to an aircraft component of a plurality of aircraft components and is further configured to:

receive an alternate signal from a second aircraft component of the at least an aircraft component; and

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

11. A method of distributed control with supplemental attitude adjustment, comprising:

receiving, by a plurality of aircraft components communicatively connected to a plurality of flight components, the plurality of aircraft components and the plurality of flight components located within an aircraft having an aircraft attitude, an aircraft command, wherein the aircraft command is received from a command sensor attached to an aircraft control;

generating, by the plurality of aircraft components, a response command directing the flight components as a function of an aggregate attitude, wherein the aggregate attitude combines a supplemental attitude with the aircraft attitude.

12. The method of claim 11 , further comprising an aircraft control component, the aircraft control component communicatively connected to an aircraft control, the aircraft control component configured to:

calculate the displacement of the aircraft control from a default position;

compare the displacement of the aircraft control against a first threshold; and

transmit an engagement datum to the command sensor indicating that the aircraft control is engaged if the displacement of the aircraft control exceeds the first threshold.

13. The method of claim 12 , further comprising:

comparing the displacement of the aircraft control against a second threshold, wherein the second threshold is less than the first threshold; and

transmitting an engagement datum to the command sensor indicating that the aircraft control is disengaged if the displacement of the aircraft control does not exceed the second threshold.

14. The method of claim 11 , further comprising generating the supplemental attitude as a function of an engagement datum.

15. The method of claim 14 , wherein generating the supplemental attitude further comprises:

determining that an aircraft control of the aircraft is disengaged; and

choosing a position supplemental attitude a function of the determination.

16. The method of claim 14 , wherein generating the supplemental attitude further comprises:

determining that an aircraft control of the aircraft is engaged; and

choosing a velocity supplemental attitude as a function of the determination.

17. The method of claim 16 , wherein determining the velocity supplemental attitude further comprises:

receiving a desired velocity, the desired velocity including a desired direction of movement;

receiving an actual velocity from a velocity sensor; and

generating a velocity supplemental attitude, comprising:

calculating the difference between the desired velocity and the actual velocity; and

calculating the part of the difference that is perpendicular to the desired direction of movement.

18. The method of claim 11 , wherein the plurality of aircraft components comprises a first aircraft component and a second aircraft component, and further comprising:

receiving, at the first aircraft component an alternate signal from the second aircraft component; and

commanding, by the first aircraft component, the flight component as a function of the alternate signal.

19. The method of claim 18 further comprises transmitting, by the first aircraft component, an outgoing signal to the second aircraft component, wherein the outgoing signal contains the aggregate attitude.

20. The method of claim 11 , further comprising commanding, by an aircraft component of the plurality of aircraft components, a flight component of a plurality of flight components to produce a response command based on the aggregate attitude, wherein the flight component of the plurality of flight components is attached to an aircraft component of a plurality of aircraft components and is further configured to:

receive an alternate signal from a second aircraft component of the at least an aircraft component; and

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