[en] A simpli ed analytical solution suitable for simple stacking sequences was
developed using the Euler buckling theory, the structure's equations of equilibrium and laminate
panel mathematical formulation. Comparing these results with numerical results reveals the ac-
curacy of the method and even more, allows us to validate the numerical analysis. Therefore, two
important results are obtained : a simpli ed analytical solution for the buckling problem and vali-
dation of the numerical results. Another important and novel nding is related to the in uence of
the angle ply orientation and of the cutouts, on the buckling load. Under symmetrical boundary
conditions and loading case, rectangular panels with elliptical cutouts, give better results for 90
oriented plies than for 0 oriented ones. With a compression load applied in the X direction, and
with material properties 10 times better in X direction than in Y direction, the best results are
obtained when the load is aligned with the Y direction associated to the material reference frame.
Moreover, panels with cutouts seem to behave better than panels without cutouts under certain
ply orientation angles.
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Pascan, Oana
Zhang, Weihong; Northwestern Polytechnical University, Xi'an, China
Ponthot, Jean-Philippe ; Université de Liège > Département d'aérospatiale et mécanique > LTAS-Mécanique numérique non linéaire
Language :
English
Title :
Mechanical Buckling of Composite Panels with/without Cutouts
Publication date :
2012
Journal title :
International Journal of Plant Engineering and Management