Global/local interlaminar stress analysis of a grid-stiffened composite panel

Journal Article · Mon Feb 01 04:00:00 EST 1993 · Journal of Reinforced Plastics and Composites; (United States)

DOI:https://doi.org/10.1177/073168449301200209· OSTI ID:6462944

Wiggenraad, J F.M.; Bauld, Jr, N R ^[1]

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1. National Aerospace Lab., Emmeloord (Netherlands) Clemson Univ., SC (United States)

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, is described. 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 a local model that are based on displacement and rotation data of a few nodes of the global model. A global panel was designed according to strength, stiffness, and stability criteria associated with the design of traditional aircraft wing panels. Interlaminar normal and shearing stress components, computed via the local model, were found to be well below typical tensile normal and shearing strengths of a graphite epoxy material. 8 refs.

• Research Organization: National Aeronautics and Space Administration, Hampton, VA (United States). Langley Research Center
• OSTI ID: 6462944
• Journal Information: Journal of Reinforced Plastics and Composites; (United States), Journal Name: Journal of Reinforced Plastics and Composites; (United States) Vol. 12:2; ISSN 0731-6844; ISSN JRPCDW
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
360603* -- Materials-- Properties
CALCULATION METHODS
COMPOSITE MATERIALS
DESIGN
FINITE ELEMENT METHOD
MATERIALS
NUMERICAL SOLUTION
REINFORCED MATERIALS
STRESS ANALYSIS