Metaheuristic-Based Topology Optimization of Fuselage Stiffeners using a Repairing Technique
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Abstract
This study focuses on the topology optimization of aircraft fuselage structures during the preliminary design phase. The primary objective is to minimize structural weight while maintaining performance and safety standards. Success-History-based Adaptive Differential Evolution with Linear Population Size Reduction (L-SHADE) and Finite Element Analysis (FEA) are employed as the optimizer and structural solver, respectively. Multiple load cases, including landing, roll, turn, push-down, and pull-up, are considered to ensure the fuselage can handle all maneuver loadings. Displacements, stresses, and the buckling factor are incorporated as structural constraints. A topology repairing technique is developed to address non-continuous topologies and reduce infeasible solutions during the optimization process. The proposed methodology enhances the efficiency and robustness of topology optimization in the context of aircraft fuselage design, resulting in an average structural weight reduction of 18.99% from ten optimization runs, with the best run being 43.19% weight reduction.
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This work is licensed under a Creative Commons Attribution-NonCommercial-ShareAlike 4.0 International License.
This work is licensed under a Creative Commons Attribution-NonCommercial-ShareAlike 4.0 International License.
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