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|Title:||Structural optimization of composite fuselage panel including buckling and manufacturing constraints||Authors:||Tanut Ungwattanapanit.||Keywords:||DRNTU::Engineering::Aeronautical engineering||Issue Date:||2011||Abstract:||Multidisciplinary Design Optimization (MDO) techniques were successfully developed and applied in sizing a composite fuselage panel of narrow-body airliner. The detailed finite element fuselage panel was undergone optimization process developed around gradient-based optimizer MSC Nastran SOL 200. Coupling with selected critical loadings, all relevant sizing requirements including structural strength, stability, and basic manufacturing constraints were embedded into the optimization process. Semi-analytical, closed-form buckling constraints were also integrated inside the optimization algorithms so as to gain efficient optimization process suitable for getting close optimal results in the preliminary design phase.||URI:||http://hdl.handle.net/10356/53748||Fulltext Permission:||restricted||Fulltext Availability:||With Fulltext|
|Appears in Collections:||MAE Theses|
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