A refined higher-order-theory-based finite element model is developed for modeling the dynamic response of delaminated smart composite plates. The theory assures an accurate description of displacement field and the satisfaction of stress-free boundary conditions at all free surfaces including delamination interfaces. A nonlinear induced strain model is used. Vibration control is obtained through piezoelectric layers bonded on the composite plate. The theory is implemented using a finite element technique, which allows the incorporation of practical geometries and boundary conditions, various sizes, and locations of delaminations, as well as discrete sensors and actuators. The resulting model is shown to agree well with published experimental data. Significant changes in dynamic properties are observed due to the presence of delamination.
|Original language||English (US)|
|Number of pages||7|
|State||Published - Feb 1999|
ASJC Scopus subject areas
- Aerospace Engineering