Muhanned Mahdi

• Prepared Stress and Strength Analysis Document including: Composite panel strength checking, support structure strength checking, bearing and pull through strength checking, fastener strength checking etc using Nastran Finite Element Analysis (FEA) and hand calculations and recommending changes where necessary for LifePort Twin Rotary Evacuating Carriage system onto an S-76D , Gulfstream G450 and S-92 Fuel tank sponsor and Forward Fairing Structure. • Perform model analysis of the S-92 Fire Bottle support in support of redesign effort to avoid aircraft excitation frequencies and mitigate field cracking issues.

Focus of research on design optimization and analysis of Turbine blade stress by using FEMAP, NX Nastran and Solidworks.  Developed unique concept for Turbine Blade model in Finite Element Analysis (FEA).  Worked on implementing Frequency Response Assurance Criterion (FRAC), Model Assurance Criterion (MAC) and other Criterion Applications to Model Correlation of Turbine blade model.  Implement Campbell diagram for disc and Turbine blade model by using FEMAP with NX Nastran.  Aircraft Structures Analysis: Calculation of failure margins for deflection, stress, fracture and fatigue requirements of a three spar wing-box structure using analytical methods and EXCEL.  Finite Element Analysis (FEA): Linear static and bifurcation buckling analysis of three spar hexagon shaped wing-box with spars, ribs, and stringers using FEMAP/ NX-NASTRAN.

 Research with Air Force (Turbine Blade Project ): • Run various analyses (Static, Nonlinear Static, Transient Dynamic, Frequency/Harmonic Response, Buckling and Design Optimization) by using Solidworks Premium 3D CAD Design Software, FEMAP with NX Nastran. • Implement Frequency Response Assurance Criterion (FRAC) and Model Assurance Criterion (MAC) Applications to Model Correlation of Turbine blade. • Implement Campbell diagram for disc and blade turbine model by using FEMAP with NX Nastran.  Research in the field of structural mechanics focusing on: • Structural Optimization: Weight minimization of the wing-box structure using response surface methods. • Aircraft Structures Analysis: Calculation of failure margins for deflection, stress, fracture and fatigue requirements of a three spar wing-box structure using analytical methods and EXCEL. • Finite Element Analysis (FEA): Linear static and bifurcation buckling analysis of three spar hexagon shaped wing-box with spars, ribs, and stringers using FEMAP/ NX-NASTRAN. • Vibration of Elastic Solids (Frequency Analysis): Normal modes analysis of an aircraft wing box structure using FEMAP/NASTRAN to investigates the effect of rib closures on torsion stiffness and natural vibration frequency. • Composite Structural Analysis: Performed stress analysis of composite laminate structure using MATLAB programming and FEMAP/NX.