SYMPOSIA PAPER Published: 01 January 1975
STP32331S

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

Source

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.

Author Information

Sendeckyj, GP
Air Force Flight Dynamics Laboratory, Dayton, Ohio
Richardson, MD
Air Force Flight Dynamics Laboratory, Dayton, Ohio
Pappas, JE
Air Force Flight Dynamics Laboratory, Dayton, Ohio
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Details
Developed by Committee: D30
Pages: 528–546
DOI: 10.1520/STP32331S
ISBN-EB: 978-0-8031-4660-0
ISBN-13: 978-0-8031-0309-2