Parametric and topology optimization of load bearing elements of aircraft fuselage structure

Abstract

This paper presents the weight reduction of load bearing elements of aircraft DA-62 fuselage structure using parametric and topology optimizations methods. The structural analysis of rear part of aircraft fuselage in various load calculation conditions is performed. In the first step using parametric optimization of structure, allow to reduce its mass to 15.84 %. In addition using topology optimization of optimized structure by parametric modeling added mass reduction to 32.87% of total structural mass.