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- W2019473054 abstract "This paper presents a structure design and optimization module, developed for the application inside multi-disciplinary optimization process chains. The loads necessary for sizing and optimization are calculated in CFD or aeroelastic calculations and applied on a Finite Element Model that represents all primary structural elements of a wing. The FE model is created automatically from a parametric geometry description. The deformations and inner loads of the wingbox are calculated via linear static FE calculations; geometry and loads are provided to an external sizing tool. Each component has a set of design variables with discrete design points which are permutated to get the component’s design candidates. A set of failure criteria is used to size the structure which can be made of composites or metal. The methodology is applied to the optimization of a forward swept composite for a short range aircraft and a design study comparing different stringer types and their influence on mass and structural deformation of the wing is performed." @default.
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- W2019473054 date "2014-06-13" @default.
- W2019473054 modified "2023-10-16" @default.
- W2019473054 title "Structural Optimization of Composite Wings in an automated Multi-Disciplinary Environment" @default.
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- W2019473054 doi "https://doi.org/10.2514/6.2014-2295" @default.
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