The paper presents the methodology for designing the load bearing elements of tail section of a light aircraft through the sequential application of methods of parametric and topological optimization. First, we analyzed the loads acting on the aircraft at its maneuvering in the vertical and horizontal planes. Then, for these loads, by the parametric optimization method, we selected the locations of ribs of the tail section of the aircraft, which were subsequently used to develop individual forms of ribs based on the topology optimization method. Next, we carried out parametric optimization of layup angles of polymer composite material, intended for the production of ribs. Finally, we developed a structural layout for the load bearing elements of the fuselage, which meets the criteria of minimum weight when restrictions are imposed on the level of stresses in some layers of the composite material.

The paper considers the method of designing the power set of the DA-62 aircraft tail section, which includes the stages of determining loads acting on the tail section, selecting position, shape and structure of the power elements, characteristics of the composite materials, from which they were made. The design process took into account simultaneous effect of aerodynamic and mass-inertial loads on the aircraft structure during various maneuvers. A feature of the method to determine geometric dimensions and shape of frames is introducing a combination of parametric and topological optimization techniques. To increase the structure weight efficiency, the problem of optimizing the scheme for laying the polymer composite material was solved. Physical and mechanical characteristics of the composite materials were determined by theoretical calculation using the multi-scale simulation principle.