A framework for the bi-level optimization of a generic transport aircraft fuselage using aeroelastic loads

Abstract The aeroelastic loads and design processes at the German Aerospace Center, Institute of Aeroelasticity in framework multi-disciplinary optimization are constantly evolving. New developments have been made in-house model generation tool ModGen, which allow us to create detailed fuselage models for preliminary design. As a part subsequent integrate structure our process, new optimizing has developed. process is based on bi-level approach follows global–local methodology simplify large problem. A sub-structuring procedure used define stiffened panels as independent structures local optimization. sized with stress buckling constraints consideration several load cases. Furthermore, this paper, we present physical sub-structure grouping enables reduced number panel optimizations saves considerable computational effort little compromise solution accuracy.