Accession Number : ADA305549

Title :   Minimum-Mass Design of Filamentary Composite Panels under Combined Loads: Design Procedure Based on Simplified Buckling Equations.

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

PDF Url : ADA305549

Report Date : OCT 1976

Pagination or Media Count : 54

Abstract : An analytical procedure is presented for designing hat-stiffened and corrugated panels made of composite material and subjected to longitudinal (in the direction of the stiffeners) compression and shear loadings. The procedure is based on nonlinear mathematical programing techniques and a simplified set of buckling equations. Design requirements considered are buckling, strength, and extensional and shear stiffness. Studies show the effects of specified thickness, variation of cross-section dimensions, stiffness requirements, local-buckling boundary conditions, and the effect of combined compression and shear loadings. (AN)

Descriptors :   *STRUCTURAL ANALYSIS, *SHEAR STRESSES, *BUCKLING, *GRAPHITE EPOXY COMPOSITES, STRESS STRAIN RELATIONS, MATHEMATICAL MODELS, THICKNESS, STRESS ANALYSIS, LAMINATES, MASS, LOADS(FORCES), PANELS, SHEAR MODULUS, STIFFNESS, STIFFENING, COMPOSITE STRUCTURES, FILAMENTS, DESIGN CRITERIA, FAILURE(MECHANICS), COMPRESSIVE STRENGTH, NONLINEAR PROGRAMMING, POISSON RATIO, BENDING STRESS.

Subject Categories : Laminates and Composite Materials
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE