Ultrasonic C-Scan Mesh Analysis for Composite Aircraft Defects
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Solution Overview
Problem
The evaluation of aircraft components made from composite materials, such as carbon fiber reinforced polymers, poses challenges due to issues like volume porosity, layer porosity, inclusions, and delaminations, which can affect the strength and longevity of aircraft, and existing methods are inefficient in detecting these defects quickly and accurately.
Innovation Solution
A computer system processes ultrasonic data from aircraft components using a mesh generation technique that subdivides the structural characteristics, calculates amplitude and time-of-flight data, and generates heatmaps to identify defects, allowing for clustering and statistical analysis to highlight potential issues, thereby facilitating faster identification of structural problems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If traditional ultrasonic inspection methods are used on composite aircraft components, then the inspection process is simple to implement, but the detection speed and accuracy are insufficient to efficiently identify defects such as volume porosity, layer porosity, inclusions, and delaminations
Solution Approach 1:
The inspection area is divided into multiple mesh cells of varying sizes based on structural characteristics. The mesh is further refined by subdividing cells to create a detailed grid structure that segments the inspection domain. This segmentation enables parallel processing of multiple regions simultaneously, improving inspection speed while maintaining high detection accuracy through localized analysis of each mesh cell.
Solution Approach 2:
The patent introduces a mesh-based spatial dimension to organize and process ultrasonic data. By transforming the inspection data into a mesh structure with multiple cells, the system enables multi-scale analysis and parallel computation across different spatial regions, thereby enhancing both detection precision and inspection throughput.
2Reliability
If comprehensive inspection of entire aircraft components is performed, then all potential defects are detected, but the time required for inspection increases significantly
Solution Approach 1:
The mesh generation process assigns different cell sizes and levels of detail to different regions of the aircraft component based on their structural characteristics and defect risk. Critical areas with higher defect probability receive finer mesh resolution, while less critical areas use coarser resolution. This local quality approach ensures comprehensive defect detection in high-risk zones while reducing inspection time in lower-risk areas.
Solution Approach 2:
The system performs preliminary mesh generation and refinement before actual defect detection. By pre-dividing the inspection area into optimized mesh cells and calculating amplitude and time-of-flight data for each cell in advance, the system prepares the data structure that enables rapid parallel processing during the actual inspection, thereby reducing overall inspection time while maintaining completeness.
3Measurement precision
If detailed analysis of each pixel is performed, then measurement precision is maximized, but processing complexity and computational time increase significantly
Solution Approach 1:
Instead of analyzing every pixel individually, the patent segments the image data into mesh cells that group multiple pixels together. Each mesh cell is processed as a unit, calculating amplitude and time-of-flight data for the entire cell rather than each pixel. This segmentation reduces processing complexity while maintaining precision by preserving the structural information contained in the grouped pixel data.
Solution Approach 2:
The patent extracts key features from the ultrasonic data at the mesh cell level rather than at the pixel level. By calculating amplitude and time-of-flight data for each mesh cell, the system extracts the essential defect information while discarding redundant pixel-level details. This extraction approach simplifies the processing system architecture while maintaining measurement precision for defect detection.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach enables more efficient and accurate detection of defects in aircraft components, reducing the time spent on non-defective areas and improving production efficiency by focusing inspections on critical areas, thus enhancing the reliability and longevity of aircraft components.
Implementation Method 1
obtain c-scan data of an area of the aircraft component that includes the carbon fiber reinforced polymer
Implementation Method 2
calculating, for each cell of the refined mesh, amplitude data that is based on an amplitude C-Scan
Implementation Method 3
calculating, for each cell of the refined mesh, time of flight (ToF) data that is based on a ToF C-Scan
Data Source
AI summary
A computer system is provided for processing ultrasonic data of an ultrasonic probe applied to an area of an aircraft component that includes carbon fiber reinforced polymer. C-scan data is obtained and a preliminary mesh is defined over the C-scan data by taking into account the underlying structural or mechanical characteristics of the analyzed component. The mesh is further refined and data gathered for each mesh cell. A heat map is generated based on the mesh.