System and method for distributed control of an aircraft

Patent metadata

Field	Value
Publication number	US-11281237-B1
Application number	US-202117323637-A
Country	US
Kind code	B1
Filing date	May 18, 2021
Priority date	May 18, 2021
Publication date	Mar 22, 2022
Grant date	Mar 22, 2022

Abstract

A system for distributed control of an aircraft. The system includes 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. 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 command the flight component to produce a response command.

First claim

What is claimed is:

1. A system for distributed 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
command the flight component to produce a response command, wherein producing the response command further comprises:
determining at least an aircraft response; and
producing the response command as a function of the 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.

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.

19. A system for distributed 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
command the flight component to produce a response command, wherein producing the response command further comprises:
determining at least an aircraft response; and
producing the response command as a function of the 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.

Assignees

• Beta Air Llc

Inventors

• Giroux Andrew
• Richter Timothy Gerard
• Moy Nicholas

Classifications

• Y02T50/40

  Weight reduction · CPC title

• B64C13/505

  having duplication or stand-by provisions · CPC title

• B64C13/503

  Fly-by-Wire · CPC title

• B64C13/50

  using electrical energy · CPC title

• B64C13/02

  Initiating means · CPC title