Structural optimization of composite fuselage panel including buckling and manufacturing constraints

• المؤلف الرئيسي: Tanut Ungwattanapanit.
• مؤلفون آخرون: School of Mechanical and Aerospace Engineering
• التنسيق: Theses and Dissertations
• اللغة: English
• منشور في: 2013
• الموضوعات: DRNTU::Engineering::Aeronautical engineering
• الوصول للمادة أونلاين: http://hdl.handle.net/10356/53748
• المؤسسة: Nanyang Technological University

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.