A further investigation for parametric optimization of arched and honeycomb cored sandwich composite panel for aircraft wing buckling with finite element analysis

This thesis dwells on a further necessity of the parametric optimization work of sandwich composite materials with FEA. The design of sandwich composite materials is not a new area, however, this work will pave the way for the engineers to design and size more effective wing panels, airframe geometries, composite fan blades, and other applications that need reduced weight. In the aerospace industry, sizing is a very important area for lightening the weight of the aircraft. Sizing operation is applied according to the stress and buckling criteria. The thickness of a panel may make the buckling failure mode is the critical failure mode and the buckling is generally the most critical failure mode of thin-walled structures under bending loads such as wings. However, the general applications of sizing are done for metallic materials and simple composite panels. This study explains the optimization studies used in the aviation industry. The sizing applications do not optimize the materials. Sizing operations determine the thickness of the thin-walled structures, however, the different material combinations may have less mass when they are optimized properly. This work strategy optimizes not only the thickness of the materials but also material combinations. Thus, this is a further way for consideration of materials in optimization and sizing. There is a discrimination between this methodology and mostly used sizing operations in the aerospace industry. Generally, sizing operations are done for the selected materials in the aerospace industry, also, the selected materials generally are in stock. However, the methodology used in this research is done for selecting the optimum materials, material combinations and thickness.