Project Overview
Conducted a comprehensive Finite Element Analysis (FEA) of an aircraft fuselage structure using ABAQUS to evaluate structural integrity under various loading conditions. The project focused on optimizing the fuselage design through iterative analysis of stress distribution, buckling behavior, and natural frequencies. Through strategic redesign of structural components and material optimization, achieved a 53% reduction in fuselage mass while maintaining structural integrity under all loading conditions. The analysis incorporated multiple loading scenarios including elevator forces, cabin pressurization, seat loads, and torsional effects, ensuring compliance with aerospace safety standards.
Key Responsibilities:
- Developed complex FEA models in ABAQUS, including shell elements, beam elements, and composite structures
- Performed structural optimization through iterative design of frames, stringers, and skin thickness configurations
- Analyzed multiple loading scenarios including elevator loads, cabin pressure, seat loads, and torsional effects
- Conducted comprehensive analyses for stress distribution, buckling behavior, and natural frequencies
- Evaluated and optimized structural components to achieve a 53% reduction in fuselage mass
- Created detailed technical documentation including simulation results, optimization strategies, and design recommendations
Project Gallery
Final Stress Analysis
Buckling Analysis
Frequency Analysis