STP580

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

    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.

    Keywords:

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


    Author Information:

    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


    Paper ID: STP32331S

    Committee/Subcommittee: D30.04

    DOI: 10.1520/STP32331S


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