Modal parameters identification of composite wing models using piezoelectric material

Resumo

This paper aims estimate modal parameters of thin composite wing models through experimental modal analysis (EMA) using piezoelectric materials. The wing models are flat plate based on three ply carbon-epoxy fiber in same directions. Five specimens with different unidirectional fiber nominal orientation (θk = 0°, θk = 30°, θk = 45°, θk = 60°, θk = 90°) are tested. These models were instrumented with one PZT (Lead Zirconate Titanate) actuator and one PVDF (Polyvinylidene Fluoride) sensor and results compared with vibrometer laser measurements. The orthotropic materials have different stiffness properties to each direction. These characteristics can be used to optimize or improve the dynamic behavior. Several examples, especially for aeronautic application can be cited, e.g., wings with negative deflection where fiber orientation was used to resolve divergence problem that these wings shows. An investigation about the dynamic behavior is conducted the modal parameters extracted. Using twelve points measured by vibrometer laser the vibration modes were achieved and modal assurance criterion (MAC) were calculated to assess the correlation between modes.

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