摘要
Amethodologyisimplementedtofindtheoptimumreducedweightconfigurationdesignofanoperatingstructureofacivilaircraftverticaltailfin.FE(finiteelement)basedtopologyoptimizationisexecutedtofindtheoptimummaterialdistributionofinitialdesignspaceofribbymaximizingthestiffness.Loadspertinenttotheoperatingandgroundconditionsareestimatedandapplied,consideringtheorientationofstructuralassemblymembersandbuilt-insupportsofferedinthemainstructure.Manufacturingconstraintsareincorporatedintotheoptimizationlooptogeneratepragmaticandmanufacturabledesignconfiguration.ThetopologicallyoptimizedconfigurationisthenconvertedtoCADviabledesignthroughdatareductionandsmoothingbyconvertingtoISO-surfaces.Amethodologyisalsodevisedtomodifythetopologicaloptimizedvoidsandmateriallayoutpreciselywithsplinesandfilletstoconstructmanufacturablefeaturesandavoidstressconcentrations.Theresultingnoveldesignproposalisthenanalyzedandvalidatedagainststipulatedloads,constraintsandotherdesignneeds.Resultsvalidatethenewdesignproposalasmorereliable,havingreducedweightandenhancedstructuralperformance.
出版日期
2009年01月11日（中国期刊网平台首次上网日期，不代表论文的发表时间）
