Buckling and postbuckling behaviour of a delaminated plate subjected to shear loading has been studied by means of the finite element analysis. The plate was assumed to contain either one or two circular delamintions of various diameteers and of various out-of-plane and in-plane positions. The size of the plate corresponded to the size of laminate panels used in aircraft structures. It was therefore possible to assess the practical applicability of numerous studies which focused on the buckling behaviour of substantially smaller plates. and Obsahuje seznam literatury
Buckling behaviour of a small delaminated plate subjected to compression loading has been studied by means of the finite element analysis. The study shows several trends in the effect of number, orientation and through-the-thickness position of delaminations upon the buckling response. These findings could be used for evaluation of reliability of laminate structures which might be subjected to impact loading, such as aircraft structures. and Obsahuje seznam literatury