Non-linear bending compliance of thin ply composite beams by local compression flange buckling

Journal article (2020)

Authors

F. Schadt University of Applied Sciences and Arts Northwestern Switzerland
M. Rueppel University of Applied Sciences and Arts Northwestern Switzerland
C. Brauner University of Applied Sciences and Arts Northwestern Switzerland
Y. Courvoisier ENATA Industries FZE
K. Masania University of Applied Sciences and Arts Northwestern Switzerland, Aerospace Manufacturing Technologies - Aerospace Engineering
C.A. Dransfeld University of Applied Sciences and Arts Northwestern Switzerland, Aerospace Manufacturing Technologies - Aerospace Engineering
Research Group
Aerospace Manufacturing Technologies (Aerospace Engineering) (TU Delft)
Copyright: © 2020 F. Schadt, M. Rueppel, C. Brauner, Y. Courvoisier, K. Masania, C.A. Dransfeld
DOI
help_outline
https://doi.org/10.1016/j.compstruct.2020.111995
Buckling Post-buckling Non-linear compliance Shape-adaptation Thin ply composites
More Info
expand_more

Published Date

01-05-2020

Language

English

Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Manufacturing Technologies

Abstract

Passive spanwise bending shape-adaption has the potential to increase the efficiency and manoeuvrability of vehicles with wing-like structures. By utilisation of compression flange buckling, the in-plane stiffness can be tuned to design beams with contrasting pre-buckling and post-buckling bending stiffness. The investigated concept is experimentally validated using a thin-ply laminated composite four-point bending beam, which is designed to experience compression flange buckling in the span with constant moment. The bending stiffness was reduced by more than 41% after the onset of buckling which shows the effectiveness of compression flange buckling for non-linear bending compliance.