Method of designing the composite load-bearing elements of the fuselage tail section

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.

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