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

GP Sendeckyj; MD Richardson; JE Pappas

doi:10.1520/STP32331S

SYMPOSIA PAPER Published: 01 January 1975

STP32331S

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

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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

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

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