Print Email Facebook Twitter Design and Testing of Aeroelastically Tailored Wings Under Maneuver Loading Title Design and Testing of Aeroelastically Tailored Wings Under Maneuver Loading Author Werter, N.P.M. (TU Delft Aerospace Structures & Computational Mechanics) Sodja, J. (TU Delft Aerospace Structures & Computational Mechanics) De Breuker, R. (TU Delft Aerospace Structures & Computational Mechanics) Date 2016 Abstract The goal of the present paper is to provide experimental validation data for the aeroelastic analysis of composite aeroelastically tailored wings with a closed-cell cross-sectional structure. Several rectangular wings with differ- ent skin thicknesses and composite layups are designed in order to minimise root bending moment under manoeuvre loading using an aeroelastic anal- ysis framework that closely couples a geometrically nonlinear beam model to a vortex lattice aerodynamic model. The globally convergent method of moving asymptotes is used to derive an optimised layup for the tailored wings. In addition a quasi-isotropic wing is analysed to serve as a ref- erence. Both the tailored wings and the quasi-isotropic wing have been manufactured and tested structurally and in the wind tunnel. In the wind tunnel, aerodynamic forces and moments and wing deformation have been measured to provide experimental validation data. To reference this document use: http://resolver.tudelft.nl/uuid:e0caadc8-b491-4956-a00d-7e1f6fd09b07 DOI https://doi.org/10.2514/1.J054965 ISSN 0001-1452 Source AIAA Journal: devoted to aerospace research and development, 55 (3), 1012-1025 Part of collection Institutional Repository Document type journal article Rights © 2016 N.P.M. Werter, J. Sodja, R. De Breuker Files PDF StaticExperiments.pdf 2.48 MB Close viewer /islandora/object/uuid:e0caadc8-b491-4956-a00d-7e1f6fd09b07/datastream/OBJ/view