Structural analysis of the proposed multi-layer dodecarotor UAV

In this study, structural analysis of a multilayer dodecarotor drone system is presented. In the structural analysis performed with the finite element method, a multi-body analysis was performed for the major components that make up the system in order to see the effect of the contact forces at the joints due to assembly. In this way, the mechanical behavior of the material used for the main parts of the drone under the effect of the predicted forces was examined and its minimum requirements were determined. Among these parts, currently available carbon fiber materials were used for components with standard geometry. However, more specific components with non-standard geometry are produced by additive manufacturing method using Polylactic Acid material. The forces acting on the system was predicted by considering the propeller and motor properties to be used in the system and the stress, strain and displacements occurring in the components under these forces was examined. Finally, system strength has been discussed by presenting the obtained analysis results both graphically and numerically.