This paper proposes a new system level topology optimization method based on the global search algorithm and morphing mesh technique in order to determine the optimal layout of components as well as the frame structure in the aircraft wing system. In this method, two types of design variables-morphing design variables (x_s) and topology design variables (x_t)-are defined for simultaneous design optimization of the component relocation and frame structure topology. In the first step of the proposed methodology, the genetic algorithm is used for global search on component locations considering multiple system-level performances such as aerodynamic stability (weight balance), structural safety, and proximity. Handling multiobjectives, multiple solutions can be obtained in this step. Then, in the second step, a morphing FE mesh with a sensitivity-based algorithm is used to determine the optimal topology of supporting frame structure. In this step, the component locations can be readjusted using FE Morphing approach implemented by HyperMesh, and the frame structure is found for compliance minimization using the SIMP method. This design strategy is applied to the commercial Boeing 757 aircraft wing. The wing design is intended to obtain effective packaging of multiple components while satisfying load-carrying performance and minimizing weight for energy efficiency. It is verified that the involvement of global search step expands the design space by increasing the degree of freedom to locate the components and increases the possibility of obtaining enhanced compliance. Also, topology optimization by morphing mesh improves compliance performance by 19～32%.
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