Control system and method with multiple linked inputs

• US 7,474,944 B2
• Filed: 04/04/2005
• Issued: 01/06/2009
• Est. Priority Date: 10/22/2002
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Cartmell, Daniel H., Coleman, Edward E.
• Primary Examiner(s): Nguyen; Cuong H
• Application Number:
  US11/099,684
• Publication Number:
  US 20050234607A1
• Time in Patent Office: 1,373 Days
• Field of Search: 701/3, 701/4, 701/8, 244/221, 244/175, 244/177, 244/181, 244/17.3, 244/4.R, 244/24, 244/75.1, 738/620.1, 738/620.5, 738/620.41
• US Class Current: 701/3
• CPC Class Codes: B64C 13/503 Fly-by-Wire
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions
• CPC Class Codes: B64C 13/506 overriding of personal controls; with automatic return to inoperative position
• CPC Class Codes: B64C 13/507 with artificial feel

Abstract

Methods and systems for linking input control signals, such as control signals used to control aspects of aircraft operation. In one embodiment, the method includes receiving first and second force signals corresponding to first and second forces applied to first and second controllers. The method can further include directing first and second position signals to the first and second controllers to move the first and second controllers to approximately the same positions. Each force signal is transmitted along a signal path, and the signal paths can be linked at a point where the signals on each path correspond to a quantity other that a position of a controller. The signal paths can be linked such that only one of the forces must exceed a threshold value for both controllers to be moved, and if one of the forces is outside a selected limit range, that force can be at least partially discounted.

Claims

1. A computer-implemented method for linking input control signals, comprising:

receiving a first force signal corresponding to a first force applied to a first aircraft controller;

receiving a second force signal corresponding to a second force applied to a second aircraft controller; and

linking the first force signal and the second force signal by performing the following functions;

if a difference between the first force signal and the second force signal is within a selected limit range, directing a first control signal corresponding to a combination of the first and second force signals; and

if the difference between the first force signal and the second force signal is outside the selected limit range, directing a second control signal that at least partially discounts the first force signal.

2. The method of claim 1, further comprising if the first force signal meets or exceeds a threshold value, directing a first position demand signal to the first controller to move the first controller to a first controller position, and directing a second position demand signal to the second controller to move the second controller to a second controller position independent of whether or not the second force signal meets or exceeds the threshold value, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance.

3. The method of claim 1 wherein the first and second force signals indicate forces in at least approximately the same direction, and wherein directing the second control signal includes basing the second control signal on a constant value for the first force signal.

4. The method of claim 1 wherein directing the first and second control signals includes directing the control signals to an actuator operatively coupled to an aircraft flight control surface.

5. The method of claim 1, wherein linking the first force signal and the second force signal includes summing a first value corresponding at least in part to the first force and a second value corresponding at least in part to the second force.

6. The method of claim 1, wherein linking the first force signal and the second force signal includes combining a first value corresponding to the first force and a second value corresponding to the second force by:

determining a difference between the first value and the second value; and

subtracting half the difference from the first value and multiplying the resultant by two.

7. The method of claim 1, wherein linking the first force signal and the second force signal includes combining a first value corresponding to the first force and a second value corresponding to the second force by:

determining a difference between the first value and the second value; and

adding half the difference to the second value and multiplying the resultant by two.

8. The method of claim 1, further comprising directing the first control signal to a controllable device of an aircraft.

9. The method of claim 1, further comprising directing the first control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.

10. The method of claim 1 wherein receiving the first force signal includes receiving the first force signal from a transducer operatively coupled to a movable aircraft control stick.

11. The method of claim 1 wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein directing the first and second control signals includes directing first and second position signals to the motor to move the first controller to corresponding first and second positions.

12. A computer-implemented method for linking signals from a first aircraft controller having a first neutral position and a second aircraft controller having a second neutral position, the method comprising:

receiving a first force signal corresponding to a first force applied to the first aircraft controller;

receiving a second force signal corresponding to a second force applied to the second aircraft controller; and

linking the first force signal and the second force signal by performing the following functions;

if a difference between the first force signal and the second force signal is within a selected limit range, directing a first control signal to control a state of a flight control surface, the first control signal corresponding to a combination of the first and second force signals; and

if the first force signal is outside the selected limit range, directing a second control signal to control a state of a flight control surface, the second control signal at least partially discounting the first force signal.

13. The method of claim 12, further comprising:

if the first force signal meets or exceeds a threshold value, directing a first position demand signal to the first controller to move the first controller to a first controller position independent of whether or not the second force signal meets or exceeds the threshold value; and

directing a second position demand signal to the second controller to move the second controller to a second controller position, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance.

14. The method of claim 12 wherein directing the first control signal includes directing a control signal based on a sum of the first and second values.

15. The method of claim 12 wherein linking the first force signal and the second force signal includes:

determining a difference between the first value and the second value; and

subtracting half the difference from the first value and multiplying the resultant by two.

16. The method of claim 12 wherein linking the first force signal and the second force signal includes:

determining a difference between the first value and the second value; and

adding half the difference to the second value and multiplying the resultant by two.

17. The method of claim 12, further comprising normalizing the first force signal by applying a correction factor to the first force signal if the first force signal corresponds to a selected force direction.

18. The method of claim 12, further comprising directing the first control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.

19. The method of claim 12 wherein receiving the first force signal includes receiving the first force signal from a transducer operatively coupled to a movable aircraft control stick.

20. The method of claim 12 wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein the method further comprises directing a motion signal to the motor to move the first controller to a selected position.

21. A computer-implemented method for linking signals from a first aircraft controller having a first neutral position and a second aircraft controller having a second neutral position, the method comprising:

receiving a first force signal corresponding to a first force applied to the first aircraft controller;

if the first force signal exceeds a threshold value, directing a first position demand signal to the first aircraft controller to move the first aircraft controller to a first controller position and directing a second position demand signal to a second controller to move the second aircraft controller to a second controller position, the first controller position being displaced from the first neutral position by a first distance, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance;

receiving a second force signal corresponding to a second force applied to the second aircraft controller; and

linking the first and second force signals by performing the following functions;

if a difference between the first force signal and the second force signal is within a selected limit range, directing a first control signal to control a state of a flight control surface, the first control signal corresponding to a combination of the first and second force signals and being independent of whether or not the second force signal exceeds the threshold value; and

if the difference between the first force signal and the second force signal is outside the selected limit range, directing a second control signal to control the state of the flight control surface, the second control signal at least partially discounting the first force signal.

22. The method of claim 21, wherein linking the first and second force signals include:

determining a difference between the first value and the second value; and

subtracting half the difference from the first value and multiplying the resultant by two.

23. The method of claim 21, further comprising directing the control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.

24. The method of claim 21 wherein the first and second force signals indicate forces in at least approximately opposite directions, and wherein at least partially discounting at least one of the first and second force signals includes setting the at least one force signal to a constant value.

25. The method of claim 21 wherein at least partially discounting at least one of the first and second force signals includes at least partially discounting both the first and second force signals.

26. A computer-readable medium the contents of which cause a computer to perform a method for linking signals from a first aircraft controller having a first neutral position and a second aircraft controller having a second neutral position, the method comprising:

receiving a first force signal corresponding to a first force applied to the first aircraft controller;

receiving a second force signal corresponding to a second force applied to the second aircraft controller;

if the first force signal exceeds a threshold value, directing a first position demand signal to the first aircraft controller to move the first aircraft controller to a first controller position and directing a second position demand signal to a second controller to move the second aircraft controller to a second controller position, the first controller position being displaced from the first neutral position by a first distance, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance; and

linking the first force signal and the second force signal by performing the following functions;

if a difference between the first force signal and the second force signal is within a selected limit range, directing a control signal to control a state of a flight control surface, the first control signal corresponding to a combination of the first and second force signals and being independent of whether or not the second force signal exceeds the threshold value; and

if the difference between the first force signal and the second force signal is outside the selected limit range, directing a second control signal to control the state of the flight control surface, the second control signal at least partially discounting the first force signal.

27. The computer-readable medium of claim 26, wherein the method comprises:

if the first force signal meets or exceeds a threshold value, directing a first position demand signal to the first controller to move the first controller to a first controller position, and directing a second position demand signal to the second controller to move the second controller to a second controller position, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance; and

directing the first control signal independent of whether or not the second force signal meets or exceeds the threshold value.

28. The computer-readable medium of claim 26 wherein the first and second force signals indicate forces in at least approximately the same direction and wherein at least partially discounting at least one of the first and second force signals includes selecting the at least one force to have a constant value.

29. The computer-readable medium of claim 26 wherein the first and second force signals indicate forces in at least approximately opposite directions, and wherein at least partially discounting at least one of the first and second force signals includes selecting the at least one force to have a constant value.

30. The computer-readable medium of claim 26 wherein at least partially discounting at least one of the first and second force signals includes at least partially discounting both the first and second force signals.

31. The computer-readable medium of claim 26, wherein the method further comprises directing the first control signal to an actuator operatively coupled to at least one of an aircraft pitch control surface, an aircraft yaw control surface and an aircraft roll control surface.

32. The computer-readable medium of claim 26 wherein receiving the first force signal includes receiving the first force signal from a transducer operatively coupled to a movable aircraft control stick.

33. The computer-readable medium of claim 26 wherein the first controller includes a control stick operatively coupled to a transducer and a motor, further wherein receiving the first force signal includes receiving the first force signal from the transducer, and wherein the method further comprises directing a motion signal to the motor to move the first controller to a selected position.

34. A system for controlling an aircraft flight control surface, comprising:

a first aircraft controller having a first input device configured to receive a first operator'"'"'s input command, the first input device being coupled to a first sensor to sense a force applied to the first input device, the first input device being coupled to a first motor to move the first input device from a first neutral position;

a second aircraft controller having a second input device configured to receive a second operator'"'"'s input command, the second input device being coupled to a second sensor to sense a force applied to the second input device, the second input device being coupled to a second motor to move the second input device from a second neutral position; and

a computer-readable medium operatively coupled to the first and second aircraft controllers, the computer-readable medium being configured to;

receive a first force signal corresponding to a first force applied to the first aircraft controller;

receive a second force signal corresponding to a second force applied to the second aircraft controller; and

link the first and second force signals by performing the following functions;

if a difference between the first force signal and the second force signal is within a selected limit range, direct a first control signal to control a state of the aircraft flight control surface, the first control signal corresponding to a combination of the first and second force signals; and

if a difference between the first force signal and the second force signal is outside the selected limit range, direct a second control signal to control a state of the aircraft flight control surface, the second control signal at least partially discounting the first force signal.

35. The system of claim 34, wherein the computer-readable medium is configured to:

determine if the first force signal meets or exceeds a threshold value;

if the first force signal meets or exceeds a threshold value, direct a first position signal to the first controller to move the first controller to a first controller position, and direct a second position signal to the second controller to move the second controller to a second controller position, the first controller having a first neutral position, the first controller position being displaced from the first neutral position by a first distance, the second controller having a second neutral position, the second controller position being displaced from the second neutral position by a second distance at least approximately equal to the first distance; and

direct the first control signal independent of whether or not the second force signal meets or exceeds the threshold value.