Acceptance testing of actuators using backlash and stiction measurements

• US 7,292,954 B2
• Filed: 07/27/2005
• Issued: 11/06/2007
• Est. Priority Date: 07/28/2004
• Status: Expired due to Fees

• Current Assignee: HR Textron, Inc.
• Original Assignee: HR Textron, Inc.
• Inventors: Deller, Robert W., Lee, Joon H.
• Primary Examiner(s): Barlow; John
• Assistant Examiner(s): TEIXEIRA MOFFAT, JONATHAN CHARLES
• Application Number:
  US11/190,667
• Publication Number:
  US 20060060078A1
• Time in Patent Office: 832 Days
• Field of Search: 702/115
• US Class Current: 702/115
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: F15B 19/005 Fault detection or monitoring
• CPC Class Codes: G01R 31/2829 Testing of circuits in sensor or actuator systems testing of apparatus for measuring electric or magnetic variables G01R35/00; testing of indicating or recording apparatus G01D; in airbag systems B60R21/0173; checking gas analysers G01N33/007; monitoring or fail-safe circuits for electromagnets H01F7/1844
• CPC Class Codes: G01R 31/343 in operation
• CPC Class Codes: G05B 19/4063 Monitoring general control system G05B19/4062 takes precedence
• CPC Class Codes: G05B 2219/42298 Measure backlash, time difference between point A to point B and from B to A, if too large
• CPC Class Codes: G05B 2219/45071 Aircraft, airplane, ship cleaning manipulator, paint stripping
• CPC Class Codes: G05B 23/0254 based on a quantitative model, e.g. mathematical relationships between inputs and outputs; functions: observer, Kalman filter, residual calculation, Neural Networks

Abstract

Aspects of the present invention are directed to systems, methods, and computer-readable media for measuring certain actuator system parameters of an actuator, e.g., an EMA in its working environment. Stiction and backlash are examples of such parameters, and these indicate the impending failure of an actuator system than conventional approaches of measuring the elapsed time of operation. When the measured backlash and/or stiction parameters exhibit a deleterious increase over time, e.g., by exceeding a preset threshold, imminent failure or the need for service/repair of the system is indicated.

Claims

1. A test system to acceptance test an actuator, the test system comprising:

a sensing circuit;

a controller; and

a communications medium connecting the sensing circuit and the controller, the controller being configured to;

obtain a first rate of change of an operating characteristic of the actuator, the first rate of change being based on previous measurements of actuator movement,

generate a second rate of change of the operating characteristic of the actuator from current measurements of actuator movement and at least some of the previous measurements of actuator movement, and

electronically indicate whether the actuator is in acceptable condition based on a comparison of the second rate of change and the first rate of change;

wherein the actuator is configured to install at an operating location of an aircraft;

wherein the controller is configured to obtain the first rate of change, generate the second rate of change, and electronically indicate whether the actuator is in acceptable condition while the actuator remains installed at the operating location of the aircraft and while the aircraft is on ground;

wherein the operating characteristic of the actuator is backlash of the actuator;

wherein the first rate of change is based on actuator movement over a first operating interval;

and wherein the controller, when electronically indicating whether the actuator is in acceptable condition includes, is configured to;

provide a result signal indicating whether the backlash of the actuator has substantially increased over a second operating interval, the second operating interval being substantially equal to the first operating interval.

2. A test system as in claim 1 wherein the actuator includes a motor and an output element coupled to the motor;

and wherein the controller, when generating the second rate of change, is configured to;

provide a set of motor signals to the motor of the actuator to move the output element,

measure motor positions of the motor and corresponding output element positions of the output element in response to the provided set of motor signals, and

output a current backlash measurement based on the measured motor positions and the measured corresponding output element positions.

3. A test system as in claim 2 wherein the controller, when outputting the current backlash measurement, is configured to:

determine a series of differences between the measured motor positions and the measured corresponding output elements positions; and

select a peak difference from the series of differences, the selected peak difference being the current backlash measurement.

4. A test system as in claim 3 wherein the controller, when providing the result signal, is configured to:

provide the result signal with (i) a first value when the second rate of change is less than 10% to indicate that the actuator is in acceptable condition, and (ii) a second value when the second rate of change is greater than or equal to 10% to indicate that the actuator is no longer in acceptable condition, the first value being different that the second value.

5. A test system as in claim 2, wherein the controller, when providing the set of motor signals to the motor of the actuator, is configured to:

apply a sequence of varying command profiles to the motor, the sequence including at plurality of complete sine wave cycles of a fixed amplitude, the fixed amplitude of subsequent sine waves being stepped down in even increments.

6. A test system as in claim 2, wherein the controller, when measuring the motor positions and output element positions and outputting the current backlash measurement, is configured to:

obtain frequency domain information by applying a time-domain-to-frequency-domain transform to the measured motor positions and the measured output element positions;

from the frequency domain information, compute an amplitude ratio and a phase shift between respective amplitude measurements of the measured motor positions and the measured output element positions; and

utilize an ideal backlash model to identify the backlash as a percentage of a commanded position based on the amplitude ratio and phase shift.

7. A test system to acceptance test an actuator, the test system comprising:

a sensing circuit;

a controller; and

a communications medium connecting the sensing circuit and the controller, the controller being configured to;

obtain a first rate of change of an operating characteristic of the actuator, the first rate of change being based on previous measurements of actuator movement,

generate a second rate of change of the operating characteristic of the actuator from current measurements of actuator movement and at least some of the previous measurements of actuator movement, and

electronically indicate whether the actuator is in acceptable condition based on a comparison of the second rate of change and the first rate of change;

wherein the actuator is configured to install at an operating location of an aircraft;

wherein the controller is configured to obtain the first rate of change, generate the second rate of change, and electronically indicate whether the actuator is in acceptable condition while the actuator remains installed at the operating location of the aircraft and while the aircraft is on ground;

wherein the operating characteristic of the actuator is stiction of the actuator;

wherein the first rate of change is based on actuator movement over a first operating interval;

and wherein the controller, when electronically indicating whether the actuator is in acceptable condition, is configured to;

provide a result signal indicating whether the stiction of the actuator has substantially increased over a second operating interval, the second operating interval being substantially equal to the first operating interval.

8. A test system as in claim 7 wherein the actuator includes a motor and an output element coupled to the motor;

and wherein the controller, when generating the second rate of change, is configured to;

provide a set of motor signals to the motor of the actuator to move the output element over multiple small displacements and over a large displacement,

measure response velocities of the output element in response to movements of the output element over the multiple small displacements and over the large displacement, and

output a current stiction measurement based on the measured response velocities of the output element.

9. A test system as in claim 8 wherein the controller, when outputting the current stiction measurement, is configured to:

determine a series of velocity deviations, each velocity deviation being a difference between a particular response velocity measured during movement of the output element over a particular one of the multiple small displacements and a response velocity measured during movement of the output element over the large displacement; and

select a peak velocity deviation from the series of velocity deviations, the peak velocity, deviation being the current stiction measurement.

10. A test system as in claim 9 wherein the controller, when providing the result signal, is configured to:

provide the result signal with (i) a first value when the second rate of change is less than 10% to indicate that the actuator is in acceptable condition, and (ii) a second value when the second rate of change is greater than or equal to 10% to indicate that the actuator is no longer in acceptable condition, the first value being different that the second value.

11. A test system as in claim 7, wherein:

the controller, when providing the set of motor signals to the motor of the actuator, is configured to apply the motor signals with a waveform that includes one or more sections with uniform or nearly uniform slope; and

the controller, when measuring the motor positions and output element positions and providing the result signal, is configured to (1) measure short and long segments of response velocity of the output element to form respective first and second sets of slopes, and (2) compare the first and second sets of slopes.

12. A method of acceptance testing an actuator, the method comprising:

obtaining a first rate of change of an operating characteristic of the actuator, the first rate of chance being based on previous measurements of actuator movement;

generating a second rate of change of the operating characteristic of the actuator from current measurements of actuator movement and at least some of the previous measurements of actuator movement; and

electronically indicating whether the actuator is in acceptable condition based on a comparison of the second rate of change and the first rate of change; and

installing the actuator at an operating location of an aircraft;

and wherein obtaining, generating, and electronically indicating occur while the actuator remains installed at the operating location of the aircraft and while the aircraft is on the ground;

wherein the operating characteristic of the actuator is backlash of the actuator;

wherein the first rate of change is based on actuator movement over a first operating interval;

and wherein electronically indicating whether the actuator is in acceptable condition includes;

providing a result signal indicating whether the backlash of the actuator has substantially increased over a second operating interval, the second operating interval being substantially equal to the first operating interval.

13. A method as in claim 12 wherein the actuator includes a motor and an output element coupled to the motor;

and wherein generating the second rate of change includes;

providing a set of motor signals to the motor of the actuator to move the output element,

measuring motor positions of the motor and corresponding output element positions of the output element in response to the provided set of motor signals, and

outputting a current backlash measurement based on the measured motor positions and the measured corresponding output element positions.

14. A method as in claim 13 wherein outputting the current backlash measurement includes:

determining a series of differences between the measured motor positions and the measured corresponding output elements positions; and

selecting a peak difference from the series of differences, the selected peak difference being the current backlash measurement.

15. A method as in claim 14 wherein providing the result signal includes:

providing the result signal with (i) a first value when the second rate of change is less than 10% to indicate that the actuator is in acceptable condition, and (ii) a second value when the second rate of change is greater than or equal to 10% to indicate that the actuator is no longer in acceptable condition, the first value being different that the second value.

16. A method as in claim 13, wherein providing the set of motor signals to the motor of the actuator includes:

applying a sequence of varying command profiles to the motor, the sequence including at plurality of complete sine wave cycles of a fixed amplitude, the fixed amplitude of subsequent sine waves being stepped down in even increments.

17. A method as in claim 13, wherein measuring the motor positions and output element positions and outputting the current backlash measurement includes:

obtaining frequency domain information by applying a time-domain-to-frequency-domain transform to the measured motor positions and the measured output element positions;

from the frequency domain information, computing an amplitude ratio and a phase shift between respective amplitude measurements of the measured motor positions and the measured output element positions; and

utilizing an ideal backlash model to identify the backlash as a percentage of a commanded position based on the amplitude ratio and phase shift.

18. A method of acceptance testing an actuator, the method comprising:

obtaining a first rate of change of an operating characteristic of the actuator, the first rate of change being based on previous measurements of actuator movement;

generating a second rate of change of the operating characteristic of the actuator from current measurements of actuator movement and at least some of the previous measurements of actuator movement; and

electronically indicating whether the actuator is in acceptable condition based on a comparison of the second rate of change and the first rate of change; and

installing the actuator at an operating location of an aircraft;

and wherein obtaining, generating, and electronically indicating occur while the actuator remains installed at the operating location of the aircraft and while the aircraft is on the ground;

wherein the operating characteristic of the actuator is stiction of the actuator;

wherein the first rate of change is based on actuator movement over a first operating interval;

and wherein electronically indicating whether the actuator is in acceptable condition includes;

providing a result signal indicating whether the stiction of the actuator has substantially increased over a second operating interval, the second operating interval being substantially equal to the first operating interval.

19. A method as in claim 18 wherein the actuator includes a motor and an output element coupled to the motor;

and wherein generating the second rate of change includes;

providing a set of motor signals to the motor of the actuator to move the output element over multiple small displacements and over a large displacement,

measuring response velocities of the output element in response to movements of the output element over the multiple small displacements and over the large displacement, and

outputting a current stiction measurement based on the measured response velocities of the output element.

20. A method as in claim 19 wherein outputting the current stiction measurement includes:

determining a series of velocity deviations, each velocity deviation being a difference between a particular response velocity measured during movement of the output element over a particular one of the multiple small displacements and a response velocity measured during movement of the output element over the large displacement; and

selecting a peak velocity deviation from the series of velocity deviations, the peak velocity deviation being the current stiction measurement.

21. A method as in claim 20 wherein providing the result signal includes:

providing the result signal with (i) a first value when the second rate of change is less than 10% to indicate that the actuator is in acceptable condition, and (ii) a second value when the second rate of change is greater than or equal to 10% to indicate that the actuator is no longer in acceptable condition, the first value being different that the second value.

22. A method as in claim 18, wherein:

providing the set of motor signals to the motor of the actuator includes applying the motor signals with a waveform that includes one or more sections with uniform or nearly uniform slope; and

measuring the motor positions and output element positions and providing the result signal includes (1) measuring short and long segments of response velocity of the output element to form respective first and second sets of slopes, and (2) comparing the first and second sets of slopes.