Topological Optimization of a Rear Fuselage Frame Based on Symmetrical and Unsymmetrical Load Cases

Abstract

The main subject of this work is to provide an optimal preliminary basic design for a machined frame located at the rear fuselage of an aircraft, using the topological optimization method. From several loading cases acting in the structure, only two of those were selected as the determining loading cases, both originated from the vertical empennage. The first corresponds to the aircraft vertical bending and the second to the aircraft torsion. This approach was necessary because the inclusion of all load cases in the optimization could not lead to a clear definition of the optimal design. The results obtained showed an optimal topology with strong resemblance to same purpose structures commonly found in practice.