Presently the development of fast simulation tools for the post buckling behavior of fuselages is based on panel level, typically comprising a segment of 2-3 frames and 5-10 stringers. The accurate buckling simulation of an entire fuselage is still a challenge, but required in order to reliable consider local and global influences on the stability.
The DLR-Institute of Composite Structures and Adaptive Systems investigates two different approaches:
1. Semi-analytical methods based analytical approaches for frames, skins and stringers
2. Finite Element Methods based on globally reduced domains.
The development of new simulation methods for the buckling of aircraft fuselages serves the exploitation of the structural reserves and in consequence weight reduction. .