Abstract
This article describes a global/local procedure for the computation of the interlaminar stress components at the skin-wrap, skin-core, and wrap-core interfaces for an advanced-concept stiffened panel. The procedure consists of a global model of two- dimensional shell elements that is used to design a grid-stiffened panel with blade-type stiffeners, a local model of three-dimensional solid elements that is used to compute in terlaminar stress components, and a scheme devised to assign displacement boundary con ditions for the local model that are based on displacement and rotation data of a few nodes of the global model.
Get full access to this article
View all access options for this article.
