Failure Analysis and Optimization Design of Wing Skin Unbalanced Lay-Up

To clarify the influence of unbalanced coefficient and change in lay-up angle on failure characteristics laminate static aeroelastic problem aircraft, numerical simulations were performed based classical theory Tsai-Wu criterion, as well fluid-structure coupling calculation method. The structure’s stress-strain curves are found to decrease increases. stress curve’s slope is relatively stable, whereas strain curves’ slopes three times, indicating that may be primary cause structural failure. Unbalanced laminates classified into types their mechanical properties low (Unbalanced 0.2 0.3), quasi-balanced 0.4 0.6, Balanced when 0.5), high 0.7 0.8). Within respective spanning intervals, remain stable. An increase ply reduces both elastic deformation structure factor. variation patterns at 45° 60° angles coefficients increase, opposite true for 30° angles. Finally, a two-level optimization method “equalized plies” “equal-angle was developed, resulting 23.93% reduction 37.04% laminated structure's compared preoptimization results.