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Single-level composite wing optimization based on flexural lamination parameters
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DOI：10.1007/s00158-003-0315-6.png)
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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.
Keyword:
stacking sequence optimization
composite laminate
two-level optimization
flexural lamination parameters
response surface
buckling load
combinatorial optimization
genetic algorithms
discrete design variables
composite wing structures
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