STP580: 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


    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.

    Keywords:

    composite materials, phase diagrams, nonlinear systems, stress strain diagrams, strength, laminates, mechanical properties


    Paper ID: STP32331S

    Committee/Subcommittee: D30.04

    DOI: 10.1520/STP32331S


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