Optimization Of Layout Of Main Structure Elements And Design Of Variants Of A Vertical Stabilizer Principal Construction

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 rational usage of its mechanical properties.Optimization issues will be subject to structural diagram of the aircrafts tail that is optimal fiber orientation and optimal thickness.Besides honey comb structure will be considered as an additional component of the whole algorithm.These manipulations reveal the variability of composite features.Process will be divided into stages(each section along the stiffness axis of the aircraft tail)and it will consider the most factors affecting the final result 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 depending on the specific loads.2 main ways of optimization were revealed after the various researches and experiments:gradient methods and direct search methods.However each of the ways contains advantages and disadvantages that prompted many engineers to synthesize both approaches.In this work it will be demonstrated an algorithm with a hybrid system based on several methods.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.