| Composite materials have been in wide use in aviation, ground transportation and many other areas. It is important to detect early damages to prevent major problem during flight. In this paper, attenuation coefficients of the two fundamental antisymmetric (A0) and symmetric (S0) modes were studied along 00 to 900 with 15 0 increment direction for the two types of widely Carbon Fiber Reinforced Polymer (CFRP), cross-ply and quasi-isotropic. A Scanning Laser Vibrometer (SLV) was used to determine the amplitude displacement of the Lamb wave as it propagates through the CFRP panels. The panels were excited by the lead-zirconate-titanate piezoelectric (PZT). |
