SEDL / STP / STP580-EB / STP32331S

Fracture Behavior of Thornel 300/5208 Graphite-Epoxy Laminates—Part 1: Unnotched Laminates

Sendeckyj, GP
Aerospace engineer, project engineer, and instrumentation engineer, Air Force Flight Dynamics Laboratory, Dayton, Ohio

Richardson, MD
Aerospace engineer, project engineer, and instrumentation engineer, Air Force Flight Dynamics Laboratory, Dayton, Ohio

Pappas, JE
Aerospace engineer, project engineer, and instrumentation engineer, Air Force Flight Dynamics Laboratory, Dayton, Ohio

Pages: 19    Published: Jan 1975

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Abstract

Basic stress-strain and strength data generated as part of a systematic investigation of the fracture behavior of 8-ply Thornel 300/5208 graphite-epoxy laminates are compared with theoretically predicted response curves based on single-ply stress-strain curves. Results are given for (±θ)^2s, (0/±θ/0)^s, (90/±θ/90)^s, (0/±45/90)^s, and (90/±45/0)^s laminates where θ = 0, 15, 30, 45, 60, 75, and 90 deg.