Simulation of Impact Damage in a Composite Plate and Its Detection
V. Pavelko1 I. Pavelko1 M. Smolyaninovs1 H. Pffeifer2 M. Wevers2
1Riga Technical University, Riga, Latvia
2Catholic University Leuven, Leuven, Belgium
A problem of damage prediction in aircraft structure and its non-destructive evaluation is very important for aircraft structural health assessment. The analysis of the features of direct impact of thin-walled laminate component of aircraft was performed by COMSOL Multiphysics software. Mainly the GFRC and CFRC laminates were selected in form either thin separate plate or sandwich structure. The low-velocity impact was simulated. This delamination is internal and its non-destructive detection is important for system of aircraft structural health monitoring (SHM). The simulation of A-scan and C-scan (Figure 1) procedures using ultrasound Lamb wave technology was performed. The problems of the use of GW in SHM of aircraft for damage detection in composite components are discussed.