Abstract
This article presents the deflection and stress responses of the concentric cutout impregnated composite curved/flat panel structure, including the variable cutout profiles (square, circular, and elliptical). The model can compute the structural configuration due to the curvature parameter change, i.e., plate, spherical, cylindrical, elliptical, and hyperboloid. The damaged composite structural model is derived using a cubic-order of displacement field kinematics to maintain the stress–strain continuity. The isoparametric type C0 continuous finite element (FE) modeling steps are adopted to solve the structural equilibrium equation of the cutout abided layered composite panels subjected to uniform mechanical loading via an in-house derived MATLAB code. The model accuracy has been established by comparing the deflections and the stresses with the previously published results. Finally, the layered composite shell panel's critical behavior under the static loading has been examined. Different types of numerical problems are solved by varying the associated design constraint parameter, including the cutout relevant factors (shape and size), to show the proposed model applicability.
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