Numerical and experimental nonlinear dynamic response reduction of smart composite curved structure using collocation and non-collocation configuration

In this work, a generic geometrical nonlinear mathematical model of smart composite curved shell panels has been developed for the evaluation of the linear and nonlinear dynamic responses. Further, the dynamic deflections are reduced by employing the piezoelectric material with the parent composite using two different arrangements (sensor and actuator). The current layered structure model is developed based on the higher-order mid-plane kinematics including the stretching effect. The electric potential due to the piezoelectric material included via a quadratic function of thickness for the current combined electro-elastic modeling. The geometrical distortion of the smart shell panel structure accounted via Green-Lagrange strain field including all of the nonlinear higher-order terms. The desired responses are evaluated computationally using an original computer code (MATLAB environment) with the help of the current higher-order model and finite element steps. The nonlinear dynamic deflection values are obtained through the direct iterative method in conjunction with Newmark’s integration. Additionally, the accuracy of the proposed model is demonstrated via comparison study with the available published literature with and without electric field potential. The reduction of response frequencies is also compared with the in-house experimental data. Lastly, few more numerical examples are computed for the various geometrical parameter including the shell configuration and the comprehensive behaviour of the currently developed nonlinear numerical model for the analysis of smart layered structure discussed in details.