This paper extends previous work on the integrated geometry parameterization and mesh movement strategy for aerodynamic shape optimization to high-fidelity aerostructural optimization based on steady analysis. The proposed approach allows for automatic and efficient grid movement resulting in high quality aerodynamic meshes in response to optimization shape changes and structural deflections. It is also integrated with a surface geometry parameterization that analytically describes the outer mold line at any point with a compact yet flexible set of parameters. A novel structural mesh movement algorithm has been developed, so that any jig shape changes described by the geometry parameterization can be consistently translated to the internal structures. Other components of this framework include an aerodynamic solver capable of three-dimensional inviscid and viscous flow analysis and a finite-element code for structural analysis. The aerodynamic and structural analysis modules are coupled to the linear elasticity mesh movement equations in a three-field formulation of the aerostructural problem. Gradients are computed using an augmented three-field coupled adjoint approach. Both the analysis and the adjoint problems are solved using a partitioned block Gauss-Seidel method. Results obtained by aerostructural analysis are validated with static experimental data from the High REynolds Number Aero-Structural Dynamics (HIRENASD) Project. Capabilities of the framework are demonstrated through the analysis of a flexible C-wing that is created from a planar wing using the integrated geometry parameterization and mesh movement. Finally, an in-viscid transonic wing sweep optimization study involving a large number of design variables demonstrates the ability of the methodology to capture the fundamental tradeoff between drag and weight.
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