Optimization of vertical stabilizer structure diagram

Abstract

At the present situation composite material, particularly laminate type systems are becoming increasingly important in civil aviation due to their strength and weight characteristics. However, the effectiveness of these materials depends on the rational usage of its mechanical properties. There is an optimal fiber angle in the case of ply stacking and optimal ply thickness. Both manipulations reveal the variability of composite features. This work is carried out about the optimization of aircraft structure elements. Optimization issues will cover both constituents. The process will be dividing into stages, and the most factors affecting the final result will be considered with a sight to the two main criteria (strength and weight). Using the structure diagram scheme of a vertical stabilizer, an analysis was carried out and an algorithm was developed that allows finding optimum in the structure depending on the specific loads. The optimization issues have been laid by ply stacking and thickness. Complex analysis and algorithm simplicity of the program code makes it possible to use the advantages of composite materials which showed significant weight superiority in comparison with metal analogues.