Ultimate Strength Analysis of Symmetric Laminates

Abstract

A technique is presented for predicting the response to failure of composite laminates. In this technique, cubic spline interpolation functions are used to represent basic stress-strain curves obtained from simple tests. This representation in conjunction with an incremental constitutive law is used to generate response of laminates subjected to incremental loads. The ultimate load- carrying capacity of the laminates is determined by the plywise application of a new failure criterion using strain energy under longitudinal, transverse, and shear loadings as independent parameters. Results obtained by this technique are compared with the available experimental data of boron- epoxy laminates as well as the responses generated by methods of Petit-Waddoups and Hahn. Analytical results determined by the present theory correlate with the experimental data better than those obtained by the other two techniques.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1974
Accession Number
AD0779927

Entities

People

  • R. S. Sandhu

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Biaxial Stresses
  • Civil Engineering
  • Composite Materials
  • Elastic Properties
  • Epoxy Laminates
  • Experimental Data
  • Failure Mode And Effect Analysis
  • Laminates
  • Materials
  • Materials Laboratories
  • Mechanical Properties
  • Orientation (Direction)
  • Shear Stresses
  • Stress Strain Relations
  • Stresses
  • Transverse

Fields of Study

  • Engineering

Readers

  • Approximation Theory.
  • Structural Health Monitoring of Composite Structures.