Design of a structurally optimized bioinspired structural arrangement of carbon composite fuselage of unmanned aerial vehicle based on parametric modeling

Abstract

Currently, the industry of unmanned aerial vehicles (UAV) is actively developing. They perform a wide range of different civilian and military tasks. Depending on the task, stringent requirements are imposed on the design, but the key ones are low weight, high strength and survivability. Satisfying these requirements will increase the payload mass and extend the life of the product. This can be ensured by the use of polymer composite materials (PCM) based on carbon fibers and new structural arrangement. This is especially true for the main element of the UAV frame –the fuselage. The work is devoted to an urgent task –the development of a new UAV composite structural layout. Structural-optimized structures are considered: bioinspired, auxetic, grid structures. A comparison of the developed options with the classical structure of the frame is carried out. A variant that exceeds the classical layout in terms of mass and strength up to 25% is selected. Main layout parameters are determined.