BACKUP CONTROL SYSTEM

• US 20140303812A1
• Filed: 04/05/2013
• Published: 10/09/2014
• Est. Priority Date: 04/05/2013
• Status: Abandoned Application

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Avritch, Steven A., Noll, Christopher
• Application Number:
  US13/857,281
• Publication Number:
  US 20140303812A1
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions

Abstract

An aircraft control system includes an effector module connected to a control input and a primary control module connected to the effector module. A microprocessor in the effector module provides a backup control path bypassing the primary control module when the primary control module is in a failed state.

Claims

1. An aircraft control system comprising:

a control input;

an effector module connected to said control input, said effector module including at least one microprocessor, and having at least a primary control module output, a primary control module input, and a controlled device output;

a primary control module connected to said primary control module output of said effector module and said primary control module input of said effector module, said primary control module including at least one microprocessor; and

wherein said at least one microprocessor in said effector module provides a backup control path bypassing said primary control module when said primary control module is in a failed state.

2. The aircraft control system of claim 1, wherein said at least one effector module microprocessor and said at least one primary control module microprocessor have distinct hardware architectures.

3. The aircraft control system of claim 1, wherein said effector module further comprises a flight critical sensor systems input, wherein said flight critical sensor input is one or more flight critical parameter.

4. The aircraft control system of claim 1, wherein said primary control module includes a flight critical sensor systems input, and a non flight critical sensor systems input wherein said non-flight critical sensor systems input is one or more non-flight critical parameter.

5. The aircraft control system of claim 1, wherein said effector module microprocessor includes a memory storing instructions operable to cause said effector module processor to generate a movement command based on a pilot input command from said control input when said primary control module is in a failed state.

6. The aircraft control system of claim 1, wherein each of said at least one effector module microprocessor and said primary control module microprocessor are digital controllers.

7. The aircraft control system of claim 2, further comprising:

a second control input;

a second effector module connected to said second control input, said second effector module including at least one microprocessor, and having at least a primary control module output, a primary control module input, and a controlled device output; and

a second primary control module connected to said primary control module output of said second effector module and said primary control module input of said second effector module, said primary control module including at least one microprocessor;

wherein said at least one processor in said second effector module provides a backup control path bypassing said second primary control module when said second primary control module is in a failed state.

8. The aircraft control system of claim 7, wherein each of said primary control module and said second primary control module comprises an input/output link connected to the input/output link of the other of said primary control module and said second primary control module.

9. The aircraft control system of claim 1, wherein said effector module further comprises a control input processing module, a control loop processing module, a control loop output processing module, and a control loop input processing module.

10. The aircraft control system of claim 9, wherein at least one of said input processing module, a control loop processing module, a control loop output processing module, and a control loop input processing module is a software module stored on a memory of said effector module microprocessor.

11. The aircraft control system of claim 9, wherein at least one of said input processing module, a control loop processing module, a control loop output processing module, and a control loop input processing module is a distinct physical module from said effector module microprocessor.

20. The aircraft control module of claim 1, wherein said at least one microprocessor in said effector module includes stored instructions operable to cause said at least one microprocessor in said effector module to convert a determined position instruction received at the at least one primary control module input into movement commands for an effector/actuator when a primary control module is in a non-failed state.

21. The aircraft control system of claim 20, wherein the determined position instruction is a determined position instruction output by said primary control module.

12. A method of controlling an aircraft system comprising the steps of:

receiving a pilot or autopilot input command at an effector module;

determining a movement instruction for a controlled aircraft component based on said pilot input command and at least flight critical sensor information in a microprocessor of said effector module when a primary control module is in a failed state; and

outputting said movement instruction to said controlled aircraft component, thereby controlling said controlled aircraft component.

13. The method of claim 12, further comprising the steps of:

determining a position instruction for said controlled aircraft component based on said pilot or autopilot input command, at least one flight critical sensor input and at least one non-flight critical sensor input; and

translating said position instruction to a movement instruction readable by said controlled aircraft component using an effector module processor.

14. The method of claim 13, wherein said steps of determining a position instruction for said controlled aircraft component based on said pilot input command, at least one flight critical sensor input and at least one non-flight critical sensor input, and translating said position instruction to a movement instruction readable by said controlled aircraft component using an effector module processor are performed digitally.

22. The method of claim 12, further comprising:

passing said pilot or autopilot input command from said effector module to a primary control module when said primary control module is in a non-failed state; and

determining a position instruction for said controlled aircraft component based on said pilot or autopilot input command, at least one flight critical sensor input and at least one non-flight critical sensor input using said primary control module, passing said determined position instruction from said primary control module to said effector module, and translating said position instruction to a movement instruction readable by said controlled aircraft component using an effector module processor when said primary control module is in the non-failed state.

15. An aircraft control system comprising:

a control input;

an effector module connected to said control input, said effector module including at least one microprocessor, and having at least a primary control module output, a primary control module input, and a controlled device output;

a primary control module connected to said primary control module output of said effector module and said primary control module input of said effector module, said primary control module including at least one microprocessor; and

wherein said at least one microprocessor in said effector module is operable to provide a backup control path bypassing said primary control module in response to said primary control module entering a failed state.

16. The aircraft control system of claim 15, wherein said at least one effector module microprocessor and said at least one primary control module microprocessor have distinct hardware architecture.

17. The aircraft control system of claim 15, wherein each of said at least one effector module microprocessor and said primary control module microprocessor are digital controllers.

18. The aircraft control system of claim 15, further comprising:

a second control input;

a second effector module connected to said second control input, said second effector module including at least one microprocessor, and having at least a primary control module output, a primary control module input, and a controlled device output; and

a second primary control module connected to said primary control module output of said second effector module and said primary control module input of said second effector module, said primary control module including at least one microprocessor;

wherein said at least one processor in said second effector module provides a backup control path bypassing said second primary control module when said second primary control module is in a failed state.

19. The aircraft control system of claim 18, wherein each of said primary control module and said second primary control module comprises an input/output link connected to the input/output link of the other of said primary control module and said second primary control module.

23. The aircraft control system of claim 15, wherein said at least one microprocessor in said effector module includes stored instructions operable to cause said at least one microprocessor in said effector module to convert a determined position instruction received at the at least one primary control module input into movement commands for an effector/actuator when a primary control module is in a non-failed state.