Behavior of Damaged Graphite/Epoxy Laminates Under Compression Loading.

Abstract

An experimental program was conducted to evaluate the influence of three different resin systems on the damage tolerance of graphite/polymer laminates. Testing consisted of both static compression and cyclic compression evaluation of 10.2 by 15.2- by 0.5-cm (4- by 6- by 0.2-in) laminates with circular holes, simulated delaminations, and low-velocity impact. Damage growth under steadily increasing compression and cyclic compression loading was monitored. Damage size and impact-induced failures for the three materials were compared. Of the three material systems evaluated, the one most tolerant to impact damage exhibited the least delamination within the cross section due to impact, the highest transverse tension strain to failure, and the largest crack opening force, as determined from double-cantilever-beam tests. jg p3

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1980
Accession Number
ADA303211

Entities

People

  • B. A. Byers

Organizations

  • Boeing

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Cantilever Beams
  • Commercial Aircraft
  • Composite Materials
  • Damage Tolerance
  • Epoxy Composites
  • Epoxy Laminates
  • Failure Mode And Effect Analysis
  • Laminates
  • Materials
  • Materials Processing
  • Materials Testing
  • Mechanical Working
  • Test And Evaluation
  • Transport Aircraft

Readers

  • Structural Health Monitoring of Composite Structures.