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Interlaminar stress analysis at the skin-stiffener interface of a grid-stiffened composite panelResults are presented of an analysis of the interlaminar stress components at the skin-wrap, skin-core, and wrap-core interfaces for an advanced-concept stiffened panel using a global/local finite element procedure. 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 interlaminar stress components, and a scheme devised to assign displacement boundary conditions for the local model that are derived from displacement and rotation data of a few nodes of the global model. The interlaminar stresses for this panel design were found to be well below typical tensile normal and shearing strengths of a graphite-epoxy material.
Document ID
19930040121
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wiggenraad, J. F. M.
(National Aerospace Lab. Emmeloord, Netherlands)
Bauld, N. R., Jr.
(Clemson Univ. SC, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1991
Publication Information
Publication: In: Composite structures 6; Proceedings of the 6th International Conference, Paisley College of Technology, United Kingdom, Sept. 9-11, 1991 (A93-24101 08-39)
Publisher: Elsevier Applied Science
Subject Category
Structural Mechanics
Accession Number
93A24118
Funding Number(s)
CONTRACT_GRANT: NAS1-17925
Distribution Limits
Public
Copyright
Other

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