Systems and methods of ultrasonic data evaluation of composite aircraft components

1. A method of processing ultrasonic data of an ultrasonic probe applied to an area of an aircraft component that includes carbon fiber reinforced polymer, the method comprising:

obtaining c-scan data of an area of the aircraft component that includes the carbon fiber reinforced polymer;

generating a first mesh with respect to the c-scan data, the first mesh being generated with respect to the structural characteristics of the area of the aircraft component;

generating a refined mesh by dividing cells with in the first mesh;

calculating, for each cell of the refined mesh, amplitude data that is based on an amplitude C-Scan;

calculating, for each cell of the refined mesh, time of flight (ToF) data based on a ToF C-Scan;

for a plurality of the mesh cells of the refined mesh, calculating a distance to a mean value as a function of a mean of historical values and a standard deviation of the historical values; and

generating and displaying a heatmap based on the calculated amplitude and/or ToF data, wherein each cell or group of cells of the refined mesh represents a location within the heatmap, wherein the heatmap is based on the calculated distance to the mean.

2. The method of claim 1 , wherein a first mesh cell of the generated refined mesh overlaps with other mesh cells in the generated refined mesh.

3. The method of claim 2 , wherein an amount of overlap is calculated as a function of a predetermined size of indications in data obtained from the C-Scan amplitude and/or C-Scan ToF.

4. The method of claim 1 , further comprising performing a clustering process for each mess cell, wherein the generated heatmap is based on the performed clustering process.

5. The method of claim 1 , wherein the first mesh includes differently sized mesh areas that correspond to respective structural characteristics of different areas of the aircraft component.

6. The method of claim 1 , wherein the aircraft component is a wing of the aircraft.

7. A method of processing ultrasonic data of an ultrasonic probe applied to an area of an aircraft component that includes carbon fiber reinforced polymer, the method comprising:

obtaining c-scan data of an area of the aircraft component that includes the carbon fiber reinforced polymer;

generating a first mesh with respect to the c-scan data, the first mesh being generated with respect to the structural characteristics of the area of the aircraft component;

generating a refined mesh by dividing cells with in the first mesh;

calculating, for each cell of the refined mesh, amplitude data that is based on an amplitude C-Scan;

calculating, for each cell of the refined mesh, time of flight (ToF) data that is based on a ToF C-Scan;

performing a clustering process for each mess cell, wherein the generated heatmap is based on the performed clustering process, wherein the clustering process includes:

for a plurality mesh cells, determining a first set of cells for which there are more than a threshold number of pixels with higher than an attenuation threshold;

for the first set of cells, determining whether neighboring cells have a quantity of pixels that are more than a threshold; and

forming a cluster of cells based on those ones of the first set of cells that have neighboring cells with more than the quantity, and

generating and displaying a heatmap that is based on the calculated amplitude and/or ToF data, wherein each cell or group of cells of the refined mesh represents a location within the heatmap.

8. The method of claim 7 , wherein a first mesh cell of the refined mesh overlaps with other mesh cells in the refined mesh.

9. The method of claim 8 , wherein an amount of overlap is calculated as a function of a size of indications to be detected.

10. The method of claim 7 , wherein the first mesh includes differently sized mesh areas that correspond to respective structural characteristics of different areas of the aircraft component.

11. The method of claim 7 , wherein the aircraft component is a wing of the aircraft.

12. A non-transitory computer readable storage medium storing computer readable instructions for using with a computer system that includes at least one hardware processor, the stored computer readable instructions comprising instructions that cause the computer system to:

obtain c-scan data of an area of the aircraft component that includes the carbon fiber reinforced polymer;

generate a first mesh with respect to the c-scan data, the first mesh being generated with respect to the structural characteristics of the area of the aircraft component;

generate a refined mesh by dividing cells with in the first mesh;

calculate, for each cell of the refined mesh, amplitude data that is based on an amplitude C-Scan;

calculate, for each cell of the refined mesh, time of flight (ToF) data that is based on a ToF C-Scan;

perform a clustering process for each cell of the refined mesh, wherein the clustering process includes:

for a plurality of the cells of the refined mesh, determine a first set of the cells wherein each of the cells has more than a threshold number of pixels with higher than an attenuation threshold;

for each cell of the first set of the cells, determine whether neighboring ones of the cells have a quantity of pixels more than a threshold; and

form a cluster of the cells based on those cells of the first set of cells that have neighboring cells with more than the quantity of pixels, and

generate and display a heatmap that is based on the calculated amplitude and/or ToF data, wherein each cell or group of cells of the refined mesh represents a point within the heatmap, wherein the generated heatmap is based on the clustering process.

13. The non-transitory computer readable storage medium of claim 12 , wherein a first mesh cell of the refined mesh overlaps with other mesh cells in the refined mesh.

14. The non-transitory computer readable storage medium of claim 13 , wherein an amount of overlap is calculated as a function of a predetermined size of indications in data obtained from the calculated amplitude and/or the ToF data.

15. The non-transitory computer readable storage medium of claim 12 , wherein the first mesh includes differently sized mesh areas that correspond to respective structural characteristics of different areas of the aircraft component.

16. The non-transitory computer readable storage medium of claim 12 , wherein the aircraft component is a wing of the aircraft.