Investigation of Crack Detection in Advanced Aircraft Carbon Fiber Reinforced Polymer (CFRP) Components Using Shearography and ANOVA Analysis

Carbon Fiber Reinforced Polymer (CFRP) composites are extensively used in aerospace engineering due to their high strength-to-weight ratio, durability, and resistance to fatigue and corrosion. These properties make CFRP ideal for structural components like aircraft fixed fairings, which minimize aerodynamic drag while maintaining structural integrity. However, its heterogeneous composition and complex internal structure pose challenges for non-destructive testing (NDT), especially in honeycomb-core components. Traditional methods such as Radiographic Testing (RT) and Ultrasonic Testing (UT) often lack the resolution needed for accurate defect detection. This study investigates shearography as an advanced NDT technique to improve crack detection in CFRP aircraft components. Controlled thermal stimulation using lamps of different power levels (150W, 300W, and 500W) was applied to enhance defect visibility. Shearographic analysis was conducted in multiple shearing directions (X, Y, and Z-axes) to assess crack size and location. ANOVA was used to evaluate the statistical significance of heating time on defect detection. Results indicate that higher heating power and specific shearing directions significantly influence crack visibility, with vertical cracks being more detectable in X-shearing and horizontal cracks in Y- and Z-shearing. ANOVA confirms that heating time has a statistically significant impact on defect detection accuracy.