Infrared thermographic methods for wrinkle characterization in composite structures

• US 9,519,844 B1
• Filed: 01/22/2016
• Issued: 12/13/2016
• Est. Priority Date: 01/22/2016
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Thompson, Jeffrey G., Georgeson, Gary E., Holmes, Tyler M., Tat, Hong Hue
• Primary Examiner(s): Porta, David
• Assistant Examiner(s): Sahu, Meenakshi
• Application Number:
  US15/004,119
• Time in Patent Office: 326 Days
• Field of Search: 250/338.1, 250/341.6, 250/347
• US Class Current: 1/1
• CPC Class Codes: G01J 2005/0077 Imaging
• CPC Class Codes: G01J 5/0003 for sensing the radiant heat transfer of samples, e.g. emittance meter
• CPC Class Codes: G01J 5/02 Constructional details
• CPC Class Codes: G01J 5/047 Mobile mounting; Scanning arrangements
• CPC Class Codes: G01J 5/485 Temperature profile
• CPC Class Codes: G01N 25/72 Investigating presence of flaws
• CPC Class Codes: G06F 18/22 Matching criteria, e.g. proximity measures
• CPC Class Codes: G06F 18/24 Classification techniques
• CPC Class Codes: G06T 2207/10048 Infrared image
• CPC Class Codes: G06T 2207/10132 Ultrasound image
• CPC Class Codes: G06T 2207/30164 Workpiece; Machine component
• CPC Class Codes: G06T 2207/30168 Image quality inspection
• CPC Class Codes: G06T 2207/30248 Vehicle exterior or interior
• CPC Class Codes: G06T 7/0004 Industrial image inspection
• CPC Class Codes: G06V 10/143 Sensing or illuminating at different wavelengths
• CPC Class Codes: G06V 10/764 using classification, e.g. of video objects
• CPC Class Codes: H04N 23/23 from thermal infrared radiation
• CPC Class Codes: H04N 23/56 provided with illuminating means
• CPC Class Codes: H04N 5/33 Transforming infrared radiation cameras or camera modules for generating image signals from infrared radiation H04N23/20; circuitry of SSIS for transforming infrared radiation into image signals H04N25/20
• CPC Class Codes: H04N 7/18 Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast

Abstract

Methods for identifying and quantifying wrinkles in a composite structure by processing infrared imaging data. Temperature versus time profiles for all pixels in the field of view of an infrared camera are calculated, enabling thermal signatures to be produced. By comparing the thermal signature of the part under test with the thermal signature of a reference standard representing a similar part having wrinkles of known size and shape, the presence of wrinkles can be detected. The wrinkle wavelength can be determined by measuring the infrared image and applying a transfer function. If the geometric information acquired using infrared thermography does not reach a certain quality factor (for a quality prediction) or is incomplete, an ultrasonic transducer array probe running wrinkle quantification software can be rotated into position and scanned over the wrinkle area. The ultrasonic imaging data can be combined with the infrared imaging data to enable an improved quantification of the wrinkle geometry.

Claims

1. A method for inspecting a composite structure comprising:

(a) moving an infrared camera to a location whereat a field of view of the infrared camera encompasses an inspection area on a surface of the composite structure;

(b) activating at least one flash lamp to output light that illuminates at least portions of the inspection area;

(c) activating the infrared camera to acquire infrared imaging data while the field of view of the infrared camera encompasses at least the inspection area;

(d) processing the infrared imaging data to create a thermal signature; and

(e) determining whether the thermal signature is similar within a specified threshold to any one of a multiplicity of reference thermal signatures stored in a reference database or not, the reference thermal signatures having one or more characteristics indicating the presence of wrinkles.

2. The method as recited in claim 1, wherein step (d) comprises calculating a first derivative of the infrared imaging data over time.

3. The method as recited in claim 1, wherein step (d) comprises calculating a second derivative of the infrared imaging data over time.

4. The method as recited in claim 1, further comprising accepting the composite structure if the thermal signature is not similar within the specified threshold to any one of the reference thermal signatures.

5. The method as recited in claim 1, further comprising:

(f) measuring a wavelength of wrinkles using infrared imaging data that is indicative of the presence of wrinkles under the surface of the inspected area;

(g) retrieving a transfer function from the reference database

corresponding to a reference thermal signature that is similar within the specified threshold to the thermal signature created in step (d); and

(h) applying the retrieved transfer function to the measured wavelength to estimate an actual wavelength of the wrinkles,

wherein steps (f) through (h) are performed if the thermal signature is similar within the specified threshold to any one of the reference thermal signatures.

6. The method as recited in claim 5, further comprising:

(i) moving an ultrasonic transducer array to a location whereat 15 the ultrasonic transducer array overlies the inspection area on the surface of the composite structure;

(j) activating the ultrasonic transducer array to transmit ultrasound waves into the composite structure in the inspection area;

(k) acquiring ultrasonic imaging data representing ultrasonic echoes returned from the inspection area;

(l) estimating an actual amplitude of the wrinkles based on the ultrasonic imaging data;

(m) calculating a wrinkle wavelength-to-amplitude ratio using the estimated actual wavelength and estimated actual amplitude of the wrinkles;

and

(n) determining whether the wrinkle wavelength-to-amplitude ratio calculated in step (m) is outside an allowable range or not.

7. The method as recited in claim 6, further comprising accepting the composite structure if the wrinkle wavelength-to-amplitude ratio is not outside the allowable range.

8. The method as recited in claim 6, further comprising rejecting the composite structure if the wrinkle wavelength-to-amplitude ratio is outside the allowable range.

9. The method as recited in claim 6, further comprising inputting the wrinkle wavelength-to-amplitude ratio, along with orientation information, into a stress model to model the impact of the wrinkles on performance of the composite structure.

10. A method for inspecting a composite structure comprising:

(a) acquiring infrared imaging data from an inspected area on a surface of the composite structure using an infrared camera, said infrared imaging data being indicative of the presence of wrinkles under the surface of the inspected area;

(b) processing the infrared imaging data to estimate a value of a first wrinkle dimensional parameter of the wrinkles under the surface of the composite structure in the inspected area;

(c) subsequent to step (a), acquiring ultrasonic imaging data from the inspected area on the surface of the composite structure using an ultrasonic transducer array;

(d) processing the ultrasonic imaging data to estimate a value of a second wrinkle dimensional parameter of wrinkles under the surface of the composite structure in the inspected area;

(e) calculating a value of a wrinkle parameter which is a function of the first and second wrinkle dimensional parameters; and

(f) determining a status of the composite structure in dependence on whether the value of the wrinkle parameter calculated in step (e) is inside or outside an allowable range of values.

11. The method as recited in claim 10, wherein step (c) comprises calculating a first derivative of the infrared imaging data over time.

12. The method as recited in claim 10, wherein step (c) comprises calculating a second derivative of the infrared imaging data over time.

13. The method as recited in claim 10, wherein the first wrinkle dimensional parameter is wrinkle wavelength.

14. The method as recited in claim 13, wherein the second wrinkle dimensional parameter is wrinkle amplitude.

15. The method as recited in claim 14, wherein the wrinkle parameter is a ratio of the wrinkle wavelength to the wrinkle amplitude.

16. The method as recited in claim 15, further comprising inputting the ratio of the wrinkle wavelength to the wrinkle amplitude deduced from infrared thermography time-temperature curves, along with orientation information, into a stress model to model the impact of the wrinkles on performance of the composite structure.

17. A method for measuring features in a composite structure made of a composite material and having a thickness, the method comprising:

(a) establishing a reference database containing transfer functions that relate true wrinkle wavelength to measured wrinkle wavelength in a multiplicity of reference standards made of the same composite material and having the same thickness as the composite structure to be inspected, the reference database further containing, for each transfer function, associated wrinkle dimensional data representing at least known depths, amplitudes and wavelengths of wrinkles in the multiplicity of reference standards;

(b) activating at least one flash lamp to output light that illuminates an area on a surface of the composite structure;

(c) activating an infrared camera to acquire infrared imaging data representing a temperature of the surface of the composite structure in at least a portion of the area illuminated in step (b);

(d) processing the infrared imaging data to identify the presence of wrinkles in a portion of the composite structure underneath at least a portion of the illuminated area;

(e) measuring a time required to get a maximum contrast between the wrinkled portion and a surrounding non-wrinkled portion of the composite structure;

(f) measuring a wavelength of wrinkles imaged by the infrared imaging data;

(g) estimating a depth of the wrinkled portion based on the time measured in step (e);

(h) using the estimated depth and the measured wavelength to retrieve a transfer function from the reference database; and

(i) applying the retrieved transfer function to the measured wavelength to estimate an actual wavelength of the wrinkles in the wrinkled portion of the composite structure.

18. The method as recited in claim 17, wherein step (d) comprises calculating a first derivative of the infrared imaging data over time.

19. The method as recited in claim 17, wherein step (d) comprises calculating a second derivative of the infrared imaging data over time.

20. The method as recited in claim 17, further comprising:

(j) activating an ultrasonic transducer array to transmit ultrasound waves into the wrinkled portion of the composite structure;

(k) acquiring ultrasonic imaging data representing ultrasonic echoes returned from the portion of the composite structure;

(l) estimating an actual amplitude of the wrinkles based on the ultrasonic imaging data;

(m) calculating a wrinkle wavelength-to-amplitude ratio using the estimated actual wavelength and estimated actual amplitude of the wrinkles; and

(n) determining whether the wrinkle wavelength-to-amplitude ratio calculated in step (m) is outside an allowable range or not.