Aeroelastic tailoring of composite structures

A wing-design optimization study is conducted on a composite wing. The obje ctive is to evaluate the effect of the composite layup orientation on the o ptimized weight while satisfying constraints on strength, roll-reversal vel ocity, and flutter velocity. The wing optimization studies are presented wi th the composite layups oriented at 5-deg increments up to +/-20 deg from t he midspar of the wing. The multidisciplinary optimization system, ASTROS, was used in the design study. This study, although not conclusive, indicate s that optimal designs when subjected to multiple structural constraints ar e relatively insensitive to the orientation of the laminate layup.