Accession Number : ADA289370

Title :   The Collapse of Composite Cylindrical Panels with Various Thickness using Finite Element Analysis.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s) : Chaplin, Christopher P.

PDF Url : ADA289370

Report Date : DEC 1994

Pagination or Media Count : 149

Abstract : This study compared numerical collapse results of graphite/epoxy cylindrical panels with free vertical edges undergoing axial compression for three different shell theories. Symmetric quasi-isotropic laminates were investigated using solid panels and panels with five different centralized cutouts with three thicknesses. The theories compared in the study were the Simplified Large displacement moderate Rotation (SLR) theory, the Donnell Cylindrical Shell (Modified Donnell) theory, and the Classical Donnell theory. The purpose of the study was to determine when large rotations and through-the-thickness shear become important in the numerical collapse analysis of cylindrical composite shells. By observing cases where the numerical collapse results for each of the three theories differed noticeably (>3%), it could be determined when large rotations and through-the-thickness shear were important. The effects of large rotations were noticed in nearly all of the panels with large cutouts (>3% panel area). Large rotations were also found to be important for thicker panels with either no cutout or a small cutout. The effects of through-the-thickness shear were only noticed in the thickest panels with large cutouts.

Descriptors :   *PANELS, *SHELLS(STRUCTURAL FORMS), *AIRFRAMES, *GRAPHITE EPOXY COMPOSITES, COMPRESSION, COMPUTER PROGRAMS, THICKNESS, STRESS ANALYSIS, COMPOSITE MATERIALS, LAMINATES, FINITE ELEMENT ANALYSIS, STIFFNESS, DISPLACEMENT, MODULUS OF ELASTICITY, COMPOSITE STRUCTURES, STRAIN(MECHANICS), DEGREES OF FREEDOM, SHEAR STRESSES, FAILURE(MECHANICS), ROTATION, AXIAL LOADS, COLLAPSE, POISSON RATIO.

Subject Categories : Aircraft
      Laminates and Composite Materials
      Structural Engineering and Building Technology

Distribution Statement : APPROVED FOR PUBLIC RELEASE