J. Ballmann, G. Britten, J. Hurka, M. Hesse, C. Braun

The present paper deals with the aeroelastic modelling and the development of tools for the computation of dynamic fluid-structure interaction problems, where the partial differential equations of structural dynamics and the fluid dynamics conservation laws are solved simultaneously in the time domain. The presented method aims to predict static and dynamic aeroelastic behavior as correctly as possible with reduced structural models to give support to reliable aeroelastic design. For this purpose simplified approaches like beam and plate models are used in the solid-fluidinteraction code. This is justified by the small number of structural model parameters enabling a deeper analysis of fundamental aeroelastic characteristics and yielding reliable values for design parameters. Results are presented for static divergence and limit cycle oscillations of panels, and the dynamic response and aerodynamic damping of a wing in subsonic flow. Comparison is made with the work of other authors and with aeroelastic experiments performed in a low speed wind tunnel by the Institute of Lightweight Structures of the RWTH Aachen with a highly flexible rectangular wing especially designed for validation of computational aeroelasticity.

CEAS Conference on Multidisciplinary Aircraft Design and Optimization; Köln; 2001

Book Chapter

englisch

14,8 x 21,0 cm, 10 Seiten

DGLR-Bericht, 2001, 2001-05, CEAS Conference on Multidisciplinary Aircraft Design and Optimization; S.167-176; 2001; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity, wings, structural design, aeronautics, modelling, multidisciplinary design optimisation

Bestellbar

2001