MDO analyses of wing structures for a complete aeroelastically constrained aircraft

A multidisciplinary design optimization (MDO) approach for airplane structures is presented which integrates modeling used within the structures, aerodynamics, flight dynamics, and aeroelasticity disciplines. The MDO procedure uses a numerical optimizer which includes a finite element (FE) analysis for structures, a panel method analysis for steady and unsteady aerodynamics, and an aeroelastic solver for stability and static and dynamic response. The space discretizations used in the structural and aerodynamic meshes are dynamically updated during the optimization process according to wing planform and wing structural variables. This MDO approach is primarily based on the first principles; therefore, the set of possible optimal solutions has no particular limit. The optimization capabilities of the wing planform variables compared with standard structural design variables are highlighted in this paper. Moreover, the use of composite objective functions has demonstrated the further capabilities of the presented MDO procedure. These results show that the MDO approach provides a significant, numerically efficient, and reliable tool within the framework of preliminary aircraft design.