Accession Number : ADA301714
Title : Minimum-Mass Design of Filamentary Composite Panels Under Combined Loads: Design Procedure Based on a Rigorous Buckling Analysis.
Descriptive Note : Technical note,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER
Personal Author(s) : Stroud, W. J. ; Agranoff, Nancy ; Anderson, Melvin S.
PDF Url : ADA301714
Report Date : JUL 1977
Pagination or Media Count : 42
Abstract : A procedure is presented for designing uniaxially stiffened panels made of composite material and subjected to combined inplane loads. The procedure uses a rigorous buckling analysis and nonlinear mathematical programing techniques. Design studies carried out with the procedure consider hat-stiffened and corrugated panels made of graphite-epoxy material. Combined longitudinal compression and shear and combined longitudinal and transverse compression are the loadings used in the studies. The capability to tailor the buckling response of a panel (i.e., design a panel so that it will have specified buckling loads at various buckling wavelengths) is also explored. Finally, the adequacy of another, simpler, analysis-design procedure is examined. The report demonstrates that a panel design procedure with a high-quality buckling analysis and with complete generality of constraints is practical. Such a procedure can be used to avoid failure from complex buckling modes and to determine mass and proportions of panels for multiple design load conditions and constraints. (MM)
Descriptors : *COMPOSITE MATERIALS, *COMPOSITE STRUCTURES, *BUCKLING, *GRAPHITE EPOXY COMPOSITES, COMPRESSION, COMPUTER PROGRAMS, MATHEMATICAL MODELS, LOADS(FORCES), PANELS, STRUCTURAL ANALYSIS, DEFORMATION, STIFFENING, SHEAR STRESSES, FILAMENTS, DESIGN CRITERIA, GRAPHITED MATERIALS, EPOXY RESINS, CORRUGATING.
Subject Categories : Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE