A refined 1D FE model for the application to aeroelasticity of composite wings

Varello, A, Petrolo, M and Carrera, E 2011, 'A refined 1D FE model for the application to aeroelasticity of composite wings', in M. Papadrakakis, E. Onate and B. Schrefler (ed.) Proceedings of 4th International Conference on Computational Methods for Coupled Problems in Science and Engineering: COUPLED PROBLEMS 2011, Kos, Greece, 20-22 June 2011, pp. 623-634.


Document type: Conference Paper
Collection: Conference Papers

Title A refined 1D FE model for the application to aeroelasticity of composite wings
Author(s) Varello, A
Petrolo, M
Carrera, E
Year 2011
Conference name 4th International Conference on Computational Methods for Coupled Problems in Science and Engineering: COUPLED PROBLEMS 2011
Conference location Kos, Greece
Conference dates 20-22 June 2011
Proceedings title Proceedings of 4th International Conference on Computational Methods for Coupled Problems in Science and Engineering: COUPLED PROBLEMS 2011
Editor(s) M. Papadrakakis, E. Onate and B. Schrefler
Publisher International Center for Numerical Methods in Engineering (CIMNE)
Place of publication Barcelona, Spain
Start page 623
End page 634
Total pages 12
Abstract The extension of a hierarchical one-dimensional structural model to aeroelasticity is the subject of the present paper. The aerodynamic model is based on the Vortex Lattice Method, VLM, whereas the refined 1D model is based on the Carrera Unified Formulation, CUF. Airfoil in-plane deformation and warping are introduced by enriching the displacement field over the cross-section of the wing. Linear to fourth-order expansions are adopted and classical beam theories (Euler-Bernoulli and Timoshenko) are obtained as particular cases. The VLM aerodynamic theory is coupled with the structural finite element model via an appropriate adaptation of the Infinite Plate Spline method. The aeroelastic tailoring is investigated for several wing configurations (by varying aspect ratio, airfoil geometry and sweep angle) and an excellent agreement with MD NASTRAN solution is provided for structural and aeroelastic cases. The effectiveness of higher-order models for an accurate evaluation of aeroelastic response of isotropic and composite wings is shown.
Subjects Aerospace Engineering not elsewhere classified
Keyword(s) Aeroelasticity
FE-VLM Coupling
Refined BeamModels
CompositeWings
Unified Formulation
Copyright notice © The authors
ISBN 9788489925786
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