Accession Number : ADA308217
Title : Buckling Analysis for Axially Compressed Flat Plates, Structural Sections, and Stiffened Plates Reinforced with Laminated Composites.
Descriptive Note : Contract rept.,
Corporate Author : BOEING COMMERCIAL AIRPLANE CO SEATTLE WA
Personal Author(s) : Viswanathan, A. V. ; Soong, Tsai-Chen ; Miller, R. E., Jr
PDF Url : ADA308217
Report Date : NOV 1971
Pagination or Media Count : 81
Abstract : A classical buckling analysis is developed for stiffened, flat plates composed of a series of linked flat plate and beam elements. Plates are idealized as multilayered orthotropic elements, structural beads and lips are idealized as beams. The loaded edges of the stiffened plate are simply supported and the conditions at the unloaded edges can be prescribed arbitrarily. The plate and beam elements are matched along their common junctions for displacement continuity and force equilibrium in an exact manner. Offsets between elements are considered in the analysis. Buckling under uniaxial compressive load for plates, sections and stiffened plates is investigated. Buckling loads are found as the lowest of all possible general and local failure modes and the mode shape is used to determine whether buckling is a local or general instability. Numerical correlations with existing analysis and test data for plates, sections and stiffened plates including boron-reinforced structures are discussed. In general, correlations are reasonably good.
Descriptors : *LAMINATES, *FIBER REINFORCED COMPOSITES, *BUCKLING, *FLAT PLATE MODELS, COMPRESSION, ALUMINUM ALLOYS, COMPOSITE MATERIALS, STIFFNESS, DISPLACEMENT, STIFFENING, FAILURE, COMPOSITE STRUCTURES, TITANIUM, BORON, AXIAL LOADS.
Subject Categories : Laminates and Composite Materials
Properties of Metals and Alloys
Distribution Statement : APPROVED FOR PUBLIC RELEASE