Failure Analysis of Composite Laminates with a Fastener Hole.

Abstract

Stress and strength analysis of composite laminates with a through the thickness circular hole, under uniaxial tensile load has been conducted. The hole is filled with a rigid core simulating a bolt. As a representation of the force at the bolted joint, displacement boundary conditions are applied to the rigid core. The stress analysis is based on treating the laminate as a homogeneous plate using finite element technique. The strength analysis is based on the tensor polynomial failure criterion applied to each constituent ply orientations. The ultimate laminate failure strength is based on the last ply failure stress. The resulting predictions of strength are found to be conservative as compared to experimental values. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1980
Accession Number
ADA085858

Entities

People

  • Som R. Soni

Organizations

  • Wright Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Force
  • Air Force Facilities
  • Bolted Joints
  • Composite Materials
  • Failure Mode And Effect Analysis
  • Fasteners
  • Finite Element Analysis
  • Government Procurement
  • Governments
  • Laminates
  • Materials
  • Materials Laboratories
  • Mechanics
  • Stress Analysis
  • Stress Concentration
  • Stresses

Fields of Study

  • Engineering

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Structural Health Monitoring of Composite Structures.