Boundary-Layer Effects in Composite Laminates: Free-Edge Stress Singularities. Part 6.

Abstract

A rigorous mathematical model has been obtained for the boundary-layer free-edge stress singularity in angleplied and crossplied fiber composite laminates. The solution was obtained using the previously developed method (under the grant) consisting of complex-variable stress function potentials and unique eigenfunction expansions. The required order of the boundary-layer stress singularity is determined by solving the transcendental characteristic equation obtained from the homogeneous solution of the partial differential equations. Numerical results obtained show that the boundary-layer stress singularity depends only upon material elastic constants and fiber orientation of the adjacent plies. For angleplied and crossplied laminates the order of the singularity is weak in general. (MM)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1981
Accession Number
ADA303102

Entities

People

  • I. Choi
  • S. S. Wang

Organizations

  • University of Illinois Urbana–Champaign

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Composite Materials
  • Differential Equations
  • Eigenvalues
  • Elastic Properties
  • Epoxy Composites
  • Equations
  • Finite Element Analysis
  • Graphite Epoxy Composites
  • Jet Propulsion
  • Laminates
  • Materials
  • Materials Laboratories
  • Mechanical Properties
  • Mechanics
  • Partial Differential Equations

Fields of Study

  • Mathematics
  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Fluid Dynamics.
  • Structural Health Monitoring of Composite Structures.