Optimal Weight Design and Structural Analysis of Aircraft Fuselage Floor I-Beam: A Structural Optimization Approach

In the present study, the optimal weight design and analysis of the aircraft fuselage floor I-beam structure using an optimization approach were done. A detailed structural analysis of the existing I-beam was done to evaluate its performance under various loading conditions. The primary objective is to enhance the structural efficiency of the fuselage I-beam while reducing its weight through the utilization of optimization tools and techniques employed in ANSYS software. The critical load cases that the floor I-beam experiences during normal flight operations are identified and analyzed to determine the areas of potential weakness in the current design. The results of the normal modal analysis highlight the potential of the optimized aluminum I-beam and CFRP I-beam designs in achieving higher natural frequencies, improved stiffness, and resistance to deformation as compared to the standard design. In linear static analysis, determining the stress distribution, deflection, and overall structural integrity, the validated and optimized designs are presented as recommendations for modifying the aircraft fuselage floor I-beam section. The findings of this project aim to enhance the structural performance, integrity, and efficiency of the aircraft fuselage floor I-beam, leading to improved safety, high strength, reduced weight, and potentially enhanced fuel efficiency for the aircraft.