Authors: B Liu RT Haftka
Publish Date: 2004/01/01
Volume: 26, Issue: 1-2, Pages: 111-120
Abstract
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 0° ±45° and 90° plies are given The singlelevel optimization based on continuous flexural lamination parameters for the minimization of wing weight is compared with a twolevel optimization using response surfaces of maximal buckling load for a simple wing box design example Reasonable agreement between the two procedures indicates that the twolevel approach leads to nearoptimal designs
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