Design and Testing of Aeroelastically Tailored Wings Under Maneuver Loading

Journal article (2016)

Authors

N.P.M. Werter Aerospace Structures & Computational Mechanics - Aerospace Engineering
J. Sodja Aerospace Structures & Computational Mechanics - Aerospace Engineering
R. De Breuker Aerospace Structures & Computational Mechanics - Aerospace Engineering
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
Copyright: © 2016 N.P.M. Werter, J. Sodja, R. De Breuker
DOI: https://doi.org/10.2514/1.J054965
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Published Date

2016

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

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.

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