Design and Analysis of Multi-Layered Composite Panels for In-Plane Loadings

Abstract

Composites have a wide range of applications in the field of robotics, aerospace, aviation, sports, and automotive engineering. They have appealing properties such as high strength to weight ratio, good mechanical and electrical properties, and durability. Multilayered composites are prepared by stacking different layers of composites along different directions. This research focuses on the compression and tension response of multilayered composite panels without interference of bending by using in-plane loading. The aim of this research is to develop a generalized MATLAB code for a number of layers, to solve a model composite through analytical and MATLAB computations, to analyze the stress behavior in ANSYS (ACP) and finally to compare the results. For carrying out the analysis, a multi-layered, symmetric composite panel is modelled under in-plane loading. First, a mathematical model is formulized to solve the multi-layered composite panel under in-plane loading and analytical results are obtained. Next, a generic MATLAB code is developed, followed by simulations and computational study using ANSYS (ACP) module. The results of MATLAB and the solution of the mathematical model are found to be identical. Further, the results obtained from ANSYS (ACP) have shown the stresses in each layer and overall deformation of the composite panel. The overall results from three methods have shown that the stresses produced in a composite panel are symmetric across mirrored layers. However, there is a significant difference between the analytical and ANSYS (ACP) results, this is due to the limitations of the Classical Laminate Theory (CLT) which has been used in the analytical study. CLT does not take into effect the out-of-plane stresses. However, in real life scenarios, out-of-plane stresses exist under the in-plane loadings and have a significant effect around the edges and corners of the panel. If 10 percent of the edges are removed on both sides, the analytical results and simulations are found to be in good agreement. Further, after the ANSYS (ACP) analysis has been obtained for the panel, a sandwiched composite panel has been modelled by adding a core material of foam and polyethylene at the center of the composite. The thickness of the core material is varied to observe the change in the stress behavior. The results have shown that there is an increased stress behavior when a softer core is used or the thickness of the core material is increased.