Please use this identifier to cite or link to this item: https://hdl.handle.net/10356/53748
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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