04.2 - Aerostructures Design, Structural Dynamics, Aeroelasticity
ACHIEVEMENTS IN THE BUCKLING OF THIN-WALLED COMPOSITE LAUNCHER STRUCTURES
R. Degenhardt¹, F. Franzoni¹, S.G.P. Castro, TU-Delft, Netherlands; ¹DLR, Germany
For most structural parts of real launcher structures buckling is the critical design criterion. Due to the high imperfection sensitivity it is still today a challenge to predict a reliable buckling load. The space industry is looking for new and alternative methods. This paper presents two examples of prediction of the buckling load. The first is a fast Ritz-method and the second is a non-destructive estimation in the experiment by the vibration-correlation-technique.