ABSTRACT
L. Weiß, H. Köke & C. Hühne Institute of Composite Structures and Adaptive Systems, DLR German Aerospace Center, Braunschweig, Germany
ABSTRACT: In this paper a novel simplified structural modelling approach for stiffened panels is presented. It specifically addresses structural response of aircraft fuselage components made from carbon fibre reinforced plastics (CFRP). The proposed method considers structural modelling requirements necessary for structural optimisation with respect to system response under simultaneous static and dynamic loads. The present approach is verified through analyses of the detailed model. The results illustrate the benefits of model simplification. Replacing detailed shell model features by beam and non-linear spring elements significantly reduces computational effort. At the same time the accuracy deduction is acceptable considering topological optimisation requirements.
