Single-level composite wing optimization based on flexural lamination parameters
An optimization procedure based on flexural lamination parameters is used to integrate unstiffened composite panel design and wing structural design. The lamination parameters are constrained to a hexagonal domain when the amounts of 0degrees, +/-45degrees, and 90degrees plies are given. The single-level optimization based on continuous flexural lamination parameters for the minimization of wing weight is compared with a two-level optimization using response surfaces of maximal buckling load for a simple wing box design example. Reasonable agreement between the two procedures indicates that the two-level approach leads to near-optimal designs.
flexural lamination parameters two-level optimization response surface buckling load stacking sequence optimization composite laminate combinatorial optimization genetic algorithms discrete design variables composite wing structures