Fracture Mechanics of Matrix Cracking and Delamination in Glass/Epoxy Laminates.
Abstract
This study focused on characterizing matrix cracking and delamination behavior in multidirectional laminates. Static tension and tension-tension fatigue tests were conducted on two different layups. Damage onset, accumulation, and residual properties were measured. Matrix cracking was shown to have a considerable influence on residual stiffness of glass epoxy laminates, and could be predicted reasonably well for cracks in 90 deg plies using a simple shear lag analysis. A fracture mechanics analysis for the strain energy release rate associated with 90 deg ply matrix crack formation was developed and was shown to correlate the onset of 90 deg ply cracks in different laminates. The linear degradation of laminate modulus with delamination area, previously observed for graphite epoxy laminates, was predicted for glass epoxy laminates using a simple rule of mixtures analysis. The strain energy release rate associated with edge delamination formation under static and cyclic loading was difficult to analyze because of the presence of several contemporary damage phenomena. Keywords: Fatigue(Mechanics), and Stiffness loss.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1986
- Accession Number
- ADA173408
Entities
People
- C. Zanotti
- M. Caslini
- T. K. O'brien
Organizations
- National Aeronautics and Space Administration