Fatigue Behavior and Failure Mechanisms of Centrally Notched (0)8 and (0/90)2(S) Silicon Carbide Reinforced Aluminosilicate Glass

Abstract

Unidirectional and bidirectional notched laminates of silicon carbides/1723 were fatigue tested under tensile-tensile loading with a load ratio of 0.1. The notch, a hole, was determined to have a significant effect on 0(8) specimens. Matrix cracking developed near the theoretical maximum stress concentration points on the hole propagating parallel to the fibers, in the load direction, followed by fiber breakage. (0/90)(2)(S) specimens were found to be notched insensitive. Damage modes for this lay-up were transverse ply matrix cracking, delamination and fiber breakage in the longitudinal plies which led to specimen failure. Several existing analytical models were then applied to these laminates to predict fatigue life.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1991
Accession Number
ADA243879

Entities

People

  • William R. Moschelle

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Advanced Electronics
  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aging (Materials)
  • Ceramic Materials
  • Ceramic Matrix Composites
  • Failure Mode And Effect Analysis
  • Gas Turbines
  • Graphitic Materials
  • Material Degradation Processes
  • Materials
  • Materials Laboratories
  • Materials Processing
  • Materials Science
  • Materials Testing
  • Measurement
  • Mechanics
  • Silicon Carbide
  • Static Tests
  • Stress Strain Relations

Fields of Study

  • Materials science

Readers

  • Reinforced Composite Materials
  • Structural Health Monitoring of Composite Structures.