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- W4379876541 abstract "It is well known that the most critical phases of aircraft design are the conceptual and preliminary design stages, as these have the largest impact on both the performance and economic viability of new aircraft. To this end, the work presented herein targets the preliminary design stage, in which it is imperative to have a time-efficient multidisciplinary design optimization (MDO) capability that can support evolving design requirements, whilst also facilitating interdepartmental collaboration. As the number of disciplines included in MDO processes continues to increase, it is envisioned that some of the disciplinary tools will take the form of surrogate models, while others remain physics-based, depending on the requirements and stage of the design process. To simulate this in the context of aerostructural optimization, the current work features a high-fidelity aerodynamic flow solver, while a surrogate is employed to model the wing structure. This approach includes the evaluation of the sensitivities of both the aerodynamic and structural disciplines, using a coupled-adjoint formulation to enable gradient-based optimization. An important aspect of the method is that the surrogate is trained only once, prior to the optimization, and held fixed throughout. The surrogate model in effect parameterizes the structural design process, and outputs the structural weight and equivalent stiffness of an optimized wing structure, given inputs of global geometry parameters and sizing loads. The sizing loads used to interrogate the surrogate are represented as parameterized load envelopes, which keeps the number of surrogate inputs small and allows the surrogate to be trained using a wide variety of representative load envelopes that cover the full range of the structural design space. The new method has been implemented in the Isight process integration framework, using the NSU3D Reynolds-Averaged Navier-Stokes code for the aerodynamic analysis and adjoint implementation, and a proprietary wing structure sizing code from Bombardier Aviation. In prior work, the method was applied to the aerostructural optimization of a wing in which only the weight of the structure was taken into account. In the work presented herein, the surrogate of the wing structure models both the weight and stiffness of the structure, thereby enabling the optimization of flexible wings. The method is applied to the aerostructural optimization of the CRM configuration, illustrating the effectiveness of the method." @default.
- W4379876541 created "2023-06-09" @default.
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- W4379876541 date "2023-06-08" @default.
- W4379876541 modified "2023-09-26" @default.
- W4379876541 title "Aerostructural Wing Optimization Using a Surrogate Model of the Structure in a Coupled-Adjoint Formulation" @default.
- W4379876541 cites W2324412858 @default.
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- W4379876541 doi "https://doi.org/10.2514/6.2023-3796" @default.
- W4379876541 hasPublicationYear "2023" @default.
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