Accession Number : ADA302350

Title :   Buckling and Structural Efficiency of Sandwich-Blade Stiffened Composite Compression Panels.

Descriptive Note : Technical paper,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s) : Stein, Manuel ; Williams, Jerry G.

PDF Url : ADA302350

Report Date : SEP 1978

Pagination or Media Count : 41

Abstract : The minimum-mass structural efficiency curve is determined for sandwich-blade stiffened composite compression panels subjected to buckling and strength constraints. High structural efficiencies are attainable for this type of construction. A method of analysis is presented for the buckling of panels of this configuration which shows that buckling of such panels is strongly dependent on the through-the-thickness transverse shearing of the stiffener. Experimental results are presented from seven test specimens made of layered graphite/epoxy having stiffeners of sandwich construction with an aluminum honeycomb core, and there is good agreement between theory and experiment. (MM)

Descriptors :   *COMPOSITE MATERIALS, *BUCKLING, *GRAPHITE EPOXY COMPOSITES, *SANDWICH PANELS, COMPRESSION, DENSITY, LOAD DISTRIBUTION, LAMINATES, FINITE ELEMENT ANALYSIS, PANELS, STIFFNESS, MODULUS OF ELASTICITY, STIFFENING, COMPOSITE STRUCTURES, STRENGTH(MECHANICS), STRUCTURAL RESPONSE, ALUMINUM, SHEAR STRESSES, TORSION, TRANSVERSE, HONEYCOMB CORES.

Subject Categories : Laminates and Composite Materials
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE