Structural optimization of a aircraft’s fuselage using topology

Abstract

The main objective of this paper is to provide an optimum preliminary basic design for the central part of the fuselage structure using the topology optimization method and to check whether the design is safe or not. Several loading cases like the aerodynamic loads, structural loads etc were considered for the analysis. The central part of the fuselage was modeled using CATIA and it was analyzed using ANSYS software for different parameters like material properties, loads acting on the fuselage etc.. And even the topological parameters were applied. After the 1st analysis or the 1st iteration the model was imported back to CATIA and the regions of low stresses were removed and again analyzed and after subsequent analysis or iterations a fuselage structure with optimum material, lower stress acting regions, optimized structural volume and few other desirable objectives are obtained. Later the analysis is done to get an optimized shape and size of the fuselage.