A completely coupled thermo-piezoelectric-mechanical theory is developed to model the dynamic response of composite plates with surface-bonded piezoelectric actuators. A higher-order laminate theory is used to describe the displacement fields of both composite laminate and piezoelectric actuator layers to accurately model the transverse shear deformation, which is significant in moderately thick constructions. A higher-order temperature field is used to accurately describe the temperature distribution through the thickness of composite plates. A finite element model is developed to implement the theory. Thermal and piezoelectric loads are considered. The results obtained using this coupled theory are compared with those obtained using an uncoupled theory. Numerical results indicate that the thermo-piezoelectric-mechanical coupling has significant effect on the dynamic response of composite plates. Furthermore, coupling also affects the control authority of piezoelectric actuators.
ASJC Scopus subject areas
- Aerospace Engineering