Mathematical modeling of the strength characteristics of materials for maneuverable aircraft frames using the finite element method

Abstract

The development of the aviation industry is invariably linked to the search for new materials capable of improving the efficiency and safety of aircraft. The use of new materials for the structural frame of an aircraft is one of the most prioritized tasks for implementing composite materials, as this can reduce the aircraft’s weight, increase the internal volume of the fuselage, and simplify the integration of composites into this part of the structure due to protection from aggressive external conditions. This work provides a review of modern composite and metallic materials used in the aviation industry and analyzes their impact on the mass-dimensional characteristics of aircraft. Various types of composites (carbon fiber reinforced plastics, organic fiber reinforced plastics, metal matrix composites) and metallic alloys (aluminum, titanium, steel) are examined, with an analysis of their mechanical properties and production technologies. Special attention is given to the influence of material selection on weight, stiffness, aerodynamic drag, lift, and controllability of the aircraft. Based on a comparative analysis, the advantages and disadvantages of composite and metallic materials in aviation are identified, along with prospects for material development to enhance aerodynamic efficiency.