6th American Society for Composites Technical Conference

Conference · Wed May 01 00:00:00 EDT 1991

OSTI ID:7139582

Wiggenraad, J F.M.; Bauld, Jr, N R

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.

• Research Organization: National Aerospace Lab., Amsterdam (Netherlands)
• OSTI ID: 7139582
• Report Number(s): N-92-33139; NASA-CR-190822; NAS-1.26:190822; NLR-TP-91052-U; ETN-92-91996; CONF-9110447-; CNN: NAS1-17925
• Resource Relation: Conference: 6. American Society for Composites technical conference, Albany, NY (United States), 6-9 Oct 1991
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
33 ADVANCED PROPULSION SYSTEMS
AIRCRAFT COMPONENTS
DESIGN
COMPOSITE MATERIALS
STRESS ANALYSIS
EPOXIDES
FINITE ELEMENT METHOD
GRAPHITE
LAYERS
PANELS
REINFORCED MATERIALS
SHEAR PROPERTIES
STABILITY
TENSILE PROPERTIES
CALCULATION METHODS
CARBON
ELEMENTAL MINERALS
ELEMENTS
MATERIALS
MECHANICAL PROPERTIES
MINERALS
NONMETALS
NUMERICAL SOLUTION
ORGANIC COMPOUNDS
ORGANIC OXYGEN COMPOUNDS
360603* - Materials- Properties
330601 - Vehicle Design Factors- Body & Chassis