Abstract
A modal-based method that calculates the geometric nonlinear effects in the regime of large deformations of wing-like structures is applied to the modeling of a highly flexible 3D wingbox of high aspect ratio. The proposed method features higher-order stiffness terms and calculates the nodal deformation field not only by normal modes but also by additional modal components. In this way, a nonlinear force-displacement relationship and a geometrically nonlinear displacement field are accounted for. Static and dynamic results for the two configurations are presented together with results from a nonlinear finite element solver. The validations highlight the capability of the method to capture the nonlinear effects and demonstrates its power to model a 3D wingbox structure made of composite shell elements with anisotropic material characteristics.
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Acknowledgements
Parts of this work were carried out during two internships of the author at the Active Aeroelasticity and Structures Research Lab at the University of Michigan. The author would like to thank the entire team and especially Prof. Carlos Cesnik of the laboratory for their support. Furthermore, the support of the DLR Institute of Aeroelasticity and the LUFO IV Verbundvorhaben AeroStruct for this work is gratefully acknowledged.
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Ritter, M. (2018). A Method for the Calculation of Large Deformations in Aeroelastic Applications. In: Heinrich, R. (eds) AeroStruct: Enable and Learn How to Integrate Flexibility in Design. AeroStruct 2015. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 138. Springer, Cham. https://doi.org/10.1007/978-3-319-72020-3_17
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DOI: https://doi.org/10.1007/978-3-319-72020-3_17
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