I developed a robust MATLAB analytical tool to perform bending, torsion, and shear analysis on a single-cell uniform wing section. The study evaluated the structural response of a Cessna 172 wing under the operational envelope defined by the V-n diagram.
The analysis incorporated distributed aerodynamic loads - modeled as higher-order polynomials for lift and drag - alongside maneuvering load factors and concentrated forces to simulate wing-mounted equipment like landing gear or fuel stores.
Structural Validation & Margin of Safety
Using the modulus-weighted method, I calculated centroid locations and section properties for a complex airfoil geometry. I specifically tracked axial stress in stringer pairs and shear stress across the elliptical and flat skin panels.
I performed a comparative design study between Al 7075-T6 and Carbon/Epoxy composites. By analyzing load cases including PHAA (Positive High Angle of Attack) and NLAA (Negative Low Angle of Attack), I calculated Margins of Safety (MS) to ensure structural integrity across the operational envelope.
The tool allowed for the optimization of stringer cross-sectional areas and skin thickness to minimize weight while maintaining a positive MS and controlling tip vertical displacement and twist.
Calculated Results & Technical Specs
- • Modulus-weighted cross-section properties (EA, EI, GJ)
- • Shear center location and twist distribution
- • Internal axial, shear, bending, and torque diagrams
- • Bending displacement and slope across the wing length
- • Minimum weight optimization for aluminum vs. composite structures