Aircraft structural integrity concepts and stress analysis methods. Fail-safe vs. safe-life design. Component life estimation. Load spectra, damage tolerance. Aerodynamic manoeuvre, gust, pressurization and landing loads. V-n diagrams. Wing design: stress analysis. Strength vs. stiffness. Torsional and bending divergence. Introduction to control reversal and flutter. Fuselage analysis. Effect of cutouts. Buckling of columns, thin plates and stiffened panels under a variety of loading conditions are examined. Lab work will entail the design of aircraft primary structure. Lect: 3 hrs./Lab: 1 hr. Prerequisites: AER 504 and AER 507 and AER 520 and ECN 801 Course Weight: 1.00 Billing Units: 1
