Selection and justification of polymer composite wing load-bearing elements design parameters with material anisotropy and airload

Abstract

The rapidly developing aviation industry is looking for new design solutions in the field of designing modern passenger airliners. To ensure reliability and increase the service life of developed products can help polymer composite materials, which are already successfully used in the construction of a number of aircraft. This work is devoted to the urgent task of determining and optimizing the structural parameters of the carbon fiber wing load-bearing elements, taking into account rational reinforcement schemes. The wall thicknesses, layup patterns of unidirectional layers, the safety margins of the wing structural elements, taking into account the current operational loads for several angles of attack corresponding to different flight modes. The work is part of the methodology for designing a wing of polymer composite materials.