BUCKLING OF CIRCULAR CYLINDRICAL SHELLS WITH MULTIPLE ORTHOTROPIC LAYERS AND ECCENTRIC STIFFENERS

Abstract

An exact solution is derived for the buckling of a circular cylindrical shell with multiple orthotropic layers and eccentric stiffeners under axial compression, lateral pressure, or any combination thereof. Classical stability theory (membrane prebuckled shape) is used for simply supported edge boundary conditions. The present theory enables the study of coupling between bending and extension due to the presence of different layers in the shell and to the presence of eccentric stiffeners. Previous approaches to stiffened multilayered shells are shown to be erratic in the prediction of buckling results due to neglect of coupling between bending and extension.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1967
Accession Number
AD0660535

Entities

People

  • Robert M. Jones

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Compression
  • Computer Programs
  • Computers
  • Couplings
  • Differential Equations
  • Equations
  • Geometry
  • Hydrostatic Pressure
  • Membranes
  • Modulus Of Elasticity
  • Shape
  • Shear Modulus
  • Stiffness
  • Stress Strain Relations
  • Stresses

Fields of Study

  • Physics

Readers

  • Structural Dynamics.