Abstract
A global/local framework for multidisciplinary optimization of an aircraft wing structure has been developed. The concept of curvilinear stiffening members (spars, ribs and stiffeners) has been applied in the wing structural optimization. A global optimization framework EBF3WingOpt, which integrates the static aeroelastic, flutter and buckling analysis, has been implemented for exploiting the optimal design at the global level. The wing internal structure is optimized using curvilinear spars and ribs (SpaRibs). A two-step optimization approach, which consists of topology optimization with shape design variables and size optimization with thickness design variables, is implemented in EBF3WingOpt. A local panel optimization framework EBF3PanelOpt, which includes stress and buckling evaluation criteria, is performed to optimize the local panels for further structural weight saving. The local panel model is extracted from the global finite element model. The boundary conditions are defined on the edges of local panels using the displacement fields obtained from the global model analysis. The local panels are optimized to satisfy stress and buckling constraints. Stiffened panel with curvilinear stiffeners is implemented in EBF3PanelOpt to improve the buckling resistance of the local panels. The optimization of stiffened panels has been studied and integrated in the local optimization. The global-local optimization framework incorporates global optimization framework EBF3WingOpt and local optimization framework EBF3PanelOpt in an iterative manner. The global-local framework is developed using MATLAB and Python programming to integrate several commercial software: MSC.PATRAN for pre and post processing, MSC.NASTRAN for finite element analysis. The global-local optimization methodology is applied for NASA Common Research Model (CRM) wing. The results have shown the advantage of the multidisciplinary globallocal optimization framework in structural weight saving.
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