Substantiated Wing to Body fairing access door modification using classical laminate theory (CLT) and FeMap/NX Nastran v4.1 to obtain STC. Analysis included layer by layer stress analysis using Tsai-Wu failure criterion, Eigen value stability check, fastener loads, boundary condition substantiation, sensitivity runs, repair doubler design, and load path optimization.
- Created fuselage access panel hole modification report with stability analysis per shear buckling criterion and ring doubler design with analysis based on equivalent strength.
- Produced a pull-out table analysis report. Performed load path analysis, static equilibrium calculations, and evaluated integral vs. built-up beam concepts for the abuse load case.
- Developed A and B basis insert allowables in shear and tension for MidCoast composite honeycomb panels. Testing was performed per ASTM standards.