Analytical/Experimental Linear Bifurcation of Curved Cylindrical Composite Panels.

Abstract

The Buckling Loads of 8-ply unstiffened (Graphite-Epoxy) cylindrical panels were determined experimentally. The results were compared to the linear bifurcation loads as determined by the STAGSC-1 Computer Code. The analysis included three different ply orientations, five different aspect ratios, and one set of boundary conditions; clamped along the top and bottom curved edges and simply supported along the vertical edges. (Author)

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1982
Accession Number
ADA124664

Entities

People

  • John S. Hebert

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aeronautical Engineering
  • Air Force
  • Aspect Ratio
  • Composite Materials
  • Computers
  • Coordinate Systems
  • Curvature
  • Engineering
  • Equations
  • Modulus Of Elasticity
  • New Hampshire
  • Potential Energy
  • Sine Waves
  • Stiffness
  • Strain Gages
  • Stress Strain Relations
  • Test Fixtures

Fields of Study

  • Physics

Readers

  • Reinforced Composite Materials
  • Structural Dynamics.