Next-generation additive manufacturing technologies will enable novel, low-weight, high-performance aircraft structures. Topology optimization techniques can be used to obtain unconventional internal aircraft wing structures that can be manufactured using additive methods which depart significantly from conventional rib-spar wing constructions. However, there are significant issues that must be overcome when applying traditional topology optimization techniques to the design of aerospace structures. These challenges include efficiently solving large-scale design problems, and applying buckling criteria within a topology optimization design formulation. In this paper, we seek to address these issues by applying a scalable topology optimization method to the undeformed Common Research Model (uCRM) wing with buckling constraints applied to the skins of the wing-box. The proposed approach uses a multigrid-preconditioned Krylov method to solve the large-scale finite element analysis problem, coupled with a parallel interior-point optimizer to solve the large-scale constrained design optimization problem. This proposed method is applied to two different optimization problems: mass-constrained compliance minimization, and mass-constrained buckling-load maximization. In addition, we apply a segment-wise topology optimization design strategy to the uCRM wingbox.
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