Weight reduction in aircraft with topology optimization

One of the most important parameters in airplanes is weight. Aircraft must be light enough to perform the tasks and capabilities expected of them, while at the same time being structurally resistant to the loads they encounter. Historically, different methodologies have been tried to make lighter aircraft designs. Topology optimization has recently become a preferred weight reduction method in the aviation industry. Lighter designs are obtained by removing the material that does not provide sufficient strength to the structure from the structure. In this study, weight reduction was made in the wing area of Cessna 172 aircraft by topology optimization. Before the topology optimization phase of the wing structure, the initial weight and the forces acting on it were calculated analytically. Based on the real-life weight of the wing structure, a finite element model of its pre-optimization state was created, and its structural strength was checked. A valid model was obtained before the topology optimization by making validation analysis of the created finite element model. In topology optimization, two different topology optimizations were applied to 3-dimensional and 2-dimensional structures. In these structures, weight reduction was achieved by determining the design areas and constraints for optimization. The structure obtained from topology optimization was statically evaluated again in order not to fail.