Parametric and Topology Optimization of Polymer Composite Load Bearing Elements of Rear Part of Aircraft Fuselage Structure

This paper presents the design technique of load bearing elements of rear part of DA-62 aircraft fuselage structure. Design of load bearing elements is obtained by the combined use of parametric and topology optimization methods. Both aerodynamic and mass-inertial loads on the aircraft in various load conditions are considered in calculation process. The analysis of stress-strain condition of load-bearing elements is done in ANSYS. When using optimization methods, the weight of the load-bearing elements of the structure is reduced by 53.68 % of its original weight, while maintaining its strength properties.