SYSTEM FOR NON-DESTRUCTIVE TESTING OF COMPOSITES
Embodiments are disclosed for characterizing and quantifying composite laminate structures. The embodiments take a composite laminate of unknown ply stack composition and sequence and determine various information about the individual plies, such as ply stack, orientation, microstructure, and type. The embodiments distinguish between weave types that exhibit similar planar stiffness behaviors, but produce different failure mechanisms. Individual ply information is then used to derive the laminate bulk properties from externally provided constitutive properties of the fiber and matrix, including extensional stiffness, bending-extension coupling stiffness, bending stiffness, and the like. The laminate bulk properties are then used to generate a probabilistic failure envelope for the composite laminate. In some embodiments, ply stack type and sequence are also determined for a curved composite laminate using the disclosed embodiments by adding a rotational stage.
1 . A system for testing composite materials, comprising:
an ultrasonic transducer operable to scan a composite laminate and produce composite scan data;
a storage device connected to a processor, wherein the storage device includes an application to control the processor; and
wherein the processor receives the composite scan data from the ultrasonic transducer;
wherein the composite scan data corresponds to a nonplanar surface of the composite laminate;
wherein the processor is configured to generate a plurality of C-scan slices based on the composite scan data;
wherein the processor automatically determines at least one lamina property and at least one lamina failure parameter based on the composite scan data; and
wherein the processor generates a probabilistic failure envelope for the composite laminate using the composite scan data, the plurality of C-scan slices, the at least one lamina property, and the at least one lamina failure parameter.
2 . The system of claim 1 , wherein the processor is operable to calculate a ply type, a weave type, a number of individual laminas, or a thickness of each individual lamina using the composite scan data.
3 . The system of claim 2 , wherein the processor is operable to determine fiber and matrix moduli and/or the at least one failure parameter based on the ply type, the weave type, the number of individual laminas, or the thickness of each individual lamina calculated by the processor.
4 . The system of claim 2 , wherein the probabilistic failure envelope for the composite laminate is further based on the ply type, the weave type, the number of individual laminas, or the thickness of each individual lamina calculated by the processor.
5 . The system of claim 1 , wherein the ultrasonic transducer includes an ultrasonic pulse-wave detector.
6 . The system of claim 1 , further including a graphical user interface, wherein the graphical user interface is operable to receive a z-start time and a z-gate time of the ultrasonic transducer prior to scanning the composite laminate.
7 . The system of claim 1 , wherein the nonplanar surface of the composite laminate has a three-dimensional curvature.
8 . A system for testing composite materials, comprising:
transducer operable to scan a composite laminate and produce composite scan data; and
a processor, wherein the processor receives the composite scan data from the transducer;
wherein the processor generates at least one A-scan slice based on the composite scan data;
a graphical user interface, wherein the graphical user interface is operable to receive a z-start time and a z-gate time for the transducer prior to scanning the composite laminate;
wherein the processor generates at least one C-scan slice based on the at least one A-scan slice;
wherein the processor is configured to determine an orientation of each ply of the composite laminate; and
wherein the processor generates a probabilistic failure envelope based on the composite scan data, the at least one C-scan slice, the at least one A-scan slice, and the orientation of each ply of the composite laminate.
9 . The system of claim 8 , wherein the processor generates signal intensity data and signal time-of-flight data for a plurality of spatial locations across a surface of the composite laminate.
10 . The system of claim 9 , wherein the processor is operable to determine fiber and matrix moduli and/or failure parameters based on a ply type, a weave type, a number of individual laminas, or a thickness of each individual lamina calculated by the processor.
11 . The system of claim 9 , wherein the processor is operable to calculate a failure load for the individual laminas based on the ply type, the weave type, the number of individual laminas, or the thickness of each individual lamina calculated by the processor.
12 . The system of claim 9 , wherein the composite laminate has a nonplanar surface with a three-dimensional curvature.
13 . A system for testing composite materials, comprising:
a scanner operable to scan a composite laminate and produce composite scan data; and
a processor, wherein the processor receives the composite scan data from the scanner;
wherein the composite scan data includes signal intensity and signal time-of-flight data for a plurality of spatial locations across a surface of the composite laminate;
wherein the composite scan data corresponds to a nonplanar surface of the composite laminate;
wherein the nonplanar surface of the composite laminate has a three-dimensional curvature; and
wherein the processor determines a primary fiber orientation and a secondary fiber orientation based on the composite scan data.
14 . The system of claim 13 , wherein the processor generates at least one bulk property for the composite laminate, and wherein the at least one bulk property generated by the processor includes the extensional stiffness, the bending stiffness, or the bending-extension coupling stiffness of the composite laminate.
15 . The system of claim 13 , wherein the processor generates a probabilistic failure envelope for the composite laminate based on the composite scan data.
16 . The system of claim 13 , wherein the processor is operable to generate a ply type, a weave type, a number of individual laminas, or a thickness of each individual lamina.
17 . The system of claim 16 , wherein the processor is operable to determine fiber and matrix moduli and/or failure parameters based on the ply type, the weave type, the number of individual laminas, or the thickness of each individual lamina calculated by the processor.
18 . The system of claim 16 , wherein the processor is operable to calculate a failure load for the individual laminas based on the ply type, the weave type, the number of individual laminas, or the thickness of each individual lamina calculated by the processor.
19 . The system of claim 13 , wherein the processor determines a primary fiber orientation and a secondary fiber orientation for each C-scan of the plurality of C-scans.
20 . The system of claim 13 , wherein the processor is further operable to generate at least one A-scan slice, wherein the processor is operable to generate at least one C-scan slice based on the at least one A-scan slice, and wherein the processor is operable to analyze the at least one A-scan slice, the at least one C-scan slice, and the composite scan data to generate a failure envelope for the composite laminate.