Abstract
This thesis explores the buckling behavior of Glass Fiber/Epoxy C-section beams in general aviation, emphasizing the impact of strategic perforations and geometric enhancements on structural resilience and integrity. Employing a robust methodology, the study integrates a literature review with advanced numerical modeling using ABAQUS, complemented by experimental benchmarking. ABAQUS eigenbuckling models are meticulously validated against experimental data through mesh sensitivity analysis, achieving error margins of just 0.26% and 0.44% for buckling loads. Additionally, the mode shapes of the beams match both experimental and numerical results, ensuring high accuracy and reliability in simulation outcomes. Key findings demonstrate that optimized stiffener designs significantly improve weight efficiency and load capacity. Notably, cross stiffeners increase the buckling load by 59.5% and enhance the weight-to-strength ratio by 30.3% for perforated beams, while unperforated beams show a 21.0% increase in buckling load and a 20.1% improvement in the weight-to-strength ratio, alongside a 3.2% reduction in mass. The best longitudinal stiffener achieves a 34.5% increase in buckling load with a 7.96% mass increase for perforated beams, and balances enhancement for unperforated beams with a 2.02% increase in buckling load and a 6.10% decrease in mass. These advancements are vital for critical components like wings and landing gear supports. This work significantly contributes to the design and development of more efficient and robust aerospace structures, providing valuable insights into composite material optimization and structural enhancements.