Modelling and Analysis of Aircraft Fuselage Semi monocoque Structure

The structural integrity and performance of an aircraft fuselage are critical factors in aerospace engineering. This project focuses on the modelling and analysis of a semi-monocoque aircraft fuselage structure, a widely used design due to its high strength-to-weight ratio and efficient load distribution. The study involves creating a finite element model (FEM) of the fuselage to simulate real-world loading conditions, including aerodynamic forces, internal pressurization, and structural stresses. Various materials and geometries are considered to optimize weight, strength, and durability. Advanced simulation techniques such as ANSYS&CATIA, FEA, are employed for stress analysis, deformation studies, and failure predictions. The results provide insights into the structural behavior of semi-monocoque fuselages, aiding in weight reduction, fuel efficiency, and overall aircraft performance improvements. This research contributes to the advancement of aerospace design methodologies by ensuring safety, reliability, and cost-effectiveness in modern aircraft structures.