METHODS AND APPARATUS FOR PROVIDING SERVO TORQUE CONTROL WITH LOAD COMPENSATION FOR PILOT IN THE LOOP

• US 20160096616A1
• Filed: 10/02/2014
• Published: 04/07/2016
• Est. Priority Date: 10/02/2014
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Li, Xiaohong Linda, Stange, Kent
• Granted Patent: US 9,452,822 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 13/16 actuated automatically, e.g. responsive to gust detectors
• CPC Class Codes: B64C 13/345 with artificial feel

Abstract

A method for operating a mechanical flight control system is provided. The method provides a torque command to a servo torque control loop, wherein the servo torque control loop comprises at least one position control servo; receives at least one feedback signal from the position control servo, during operation of the position control servo; detects user external load disturbance input to the servo torque control loop, based on the at least one feedback signal; and adjusts operation of the position control servo, based on the detected user external load disturbance input.

Claims

1. A method for operating a mechanical flight control system, the method comprising:

providing a torque command to a servo torque control loop, wherein the servo torque control loop comprises at least one position control servo;

receiving at least one feedback signal from the position control servo, during operation of the position control servo;

detecting user external load disturbance input to the servo torque control loop, based on the at least one feedback signal; and

adjusting operation of the position control servo, based on the detected user external load disturbance input.

2. The method of claim 1, wherein the detecting step further comprises:

identifying an actual acceleration value and an actual velocity value of the position control servo;

determining that the actual acceleration value is greater than a programmed acceleration value of the position control servo and that the actual velocity value is greater than a programmed velocity value of the position control servo;

wherein a combination of the greater actual acceleration value and the greater actual velocity value indicates the detected user external load disturbance input.

3. The method of claim 1, wherein the detecting step further comprises:

identifying a programmed acceleration and a programmed velocity for the position control servo;

determining an actual acceleration and an actual velocity for the position control servo;

calculating a first difference between the programmed acceleration and the actual acceleration and a second difference between the programmed velocity and the actual velocity; and

when the first difference is greater than a first predetermined threshold, and the second difference is greater than a second predetermined threshold, determining that a user has provided input to the servo torque control loop.

4. The method of claim 1, further comprising:

determining whether the user external load disturbance input aids current operation of the position control servo; and

when the user external load disturbance input aids current operation of the position control servo, instructing the position control servo to provide no deterrent resistant torque.

5. The method of claim 1, further comprising:

determining whether the user external load disturbance input aids current operation of the position control servo; and

when the user external load disturbance input does not aid current operation of the position control servo, providing deterrent resistant torque.

6. The method of claim 1, wherein the detecting step further comprises:

determining whether the user external load disturbance input indicates a first increase in acceleration of the position control servo in combination with a second increase in velocity of the position control servo; and

determining that a user has provided input to the servo torque control loop, based on the indicated first increase and the indicated second increase.

7. The method of claim 1, wherein the mechanical flight control system is configured to operate within a set of flight envelope protection (FEP) limits;

and

wherein the position control servo comprises an FEP servo.

8. The method of claim 1, further comprising:

prior to operation of the position control servo, generating a servo torque command for the position control servo, based on an identified flight status of the aircraft;

detecting the user external load disturbance input; and

augmenting the servo torque command to perform the adjusting step.

9. A system for operating a servo torque control loop of an aircraft, the system comprising:

a flight envelope protection (FEP) module, configured to provide a set of FEP limits for the operation of the aircraft, wherein the servo torque control loop comprises at least one position control servo;

a feedback analysis module, configured to receive and analyze a feedback signal from the position control servo during operation of the position control servo; and

a servo control module, configured to operate the position control servo in the aircraft within the set of FEP limits provided by the FEP module, and to adjust operation of the position control servo based on analysis of the feedback analysis module.

10. The system of claim 9, wherein the feedback analysis module is further configured to detect user external load disturbance input to the servo torque control loop;

and

wherein the servo control module is further configured to control the acceleration of the position control servo based on the detected user external load disturbance input.

11. The system of claim 9, wherein the feedback analysis module is further configured to identify an actual acceleration value and an actual velocity value of the position control servo, the actual acceleration value comprising a first larger value than a programmed acceleration value of the position control servo, and the actual velocity value comprising a second larger value than a programmed velocity value of the position control servo;

wherein a combination of the first larger value and the second larger value indicates a detection of user external load disturbance input to the servo torque control loop.

12. The system of claim 9, wherein the feedback analysis module is further configured to:

identify a programmed acceleration and a programmed velocity for the position control servo;

determine an actual acceleration and an actual velocity for the position control servo;

calculate a first difference between the programmed acceleration and the actual acceleration, and a second difference between the programmed velocity and the actual velocity;

compare the first calculated difference to a first predetermined threshold value, and the second calculated difference to a second predetermined threshold value; and

when the first calculated difference is greater than the first predetermined threshold, and the second calculated difference is greater than the second predetermined threshold, determine that a user has provided external load disturbance input to the servo torque control loop.

13. The system of claim 9, wherein the feedback analysis module is further configured to:

determine whether the user external load disturbance input comprises aid to the operation of the position control servo; and

when the user external load disturbance input comprises aid to the operation of the position control servo, instruct the position control servo to provide no deterrent resistant torque.

14. The system of claim 9, wherein the feedback analysis module is further configured to:

determine whether the user external load disturbance input comprises aid to the operation of the position control servo within the set of FEP limits; and

when the user external load disturbance input does not comprise aid to the operation of the position control servo, permit transmission of a deterrent resistant torque from the position control servo.

15. The system of claim 9, wherein the feedback analysis module is further configured to determine whether the user external load disturbance input indicates a first increase in acceleration and a second increase in velocity of the position control servo;

and

wherein the servo control module is further configured to adjust operation of the position control servo based on the indicated first increase and second increase.

16. A non-transitory, computer-readable medium containing instructions thereon, which, when executed by a processor, perform a method comprising:

analyzing a feedback signal from a position control servo of a servo torque control loop of an aircraft to determine whether a user has provided external load disturbance input to the servo torque control loop, wherein the feedback signal is analyzed during operation of the position control servo;

adjusting operation of the position control servo, based on user external load disturbance input indicated by the feedback signal.

17. The non-transitory, computer-readable medium of claim 16, further comprising:

identifying a programmed acceleration and a programmed velocity for the position control servo;

determining an actual acceleration and an actual velocity for the position control servo;

calculating a first difference between the programmed acceleration and the actual acceleration and a second difference between the programmed velocity and the actual velocity;

comparing the calculated first difference to a first predetermined threshold value, and the calculated second difference to a second predetermined threshold value; and

when the calculated first difference is greater than the first predetermined threshold and the calculated second difference is greater than the second predetermined threshold, determining that a user has provided external load disturbance input to the servo torque control loop.

18. The non-transitory, computer-readable medium of claim 16, further comprising:

identifying an actual acceleration value of the position control servo and an actual velocity value of the position control servo, wherein the actual acceleration value comprises a first larger value than a programmed acceleration value of the position control servo, and wherein the actual velocity value comprises a second larger value than a programmed velocity value of the position control servo;

wherein a condition of the first larger value and the second larger value indicates the indicated user input.

19. The non-transitory, computer-readable medium of claim 16, further comprising:

determining whether the user external load disturbance input indicates differences in acceleration and velocity of the position control servo; and

performing the adjusting step based on the indicated differences in acceleration and velocity.

20. The non-transitory, computer-readable medium of claim 16, further comprising:

prior to operation of the position control servo, generating a servo torque command for the position control servo, based on an identified flight status of the aircraft;

detecting the user external load disturbance input; and

augmenting the servo torque command to perform the adjusting the position control servo.