STP1383

    Open Hole Compression Strength and Failure Characterization in Carbon/Epoxy Tape Laminates

    Published: Jan 2001


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    Abstract

    Open hole compression (OHC) design criteria often size the thicknesses of composite aircraft skin structures. Therefore, there can be a significant payoff in improving OHC allowables through better characterization of OHC strength and behavior. This study, using progressive damage analysis and empirical methods, provides new insight into OHC strength and failure behavior.

    OHC failure behavior was modeled using PDHOLEC, a progressive damage, 2-D finite-element code. Ultimate strength predictions were combined into carpet plots over a wide range of layups in three graphite composite material systems. A detailed evaluation of PDHOLEC progressive failure output resulted in the identification of several distinct predicted failure mechanisms. Predicted failure mechanisms and ultimate strengths are compared with OHC test data.

    Two distinct failure mechanisms for OHC configurations were identified based on the PDHOLEC ailure study and strength trend studies of test data: a 0° ply kinking/buckling failure mechanism and a matrix cracking mechanism. The PDHOLEC predictions and test data were grouped by the identified failure mechanisms. Then curve fit equations were generated to characterize the ultimate strength behavior for each failure mechanism.

    Keywords:

    composites, stress concentrations, compression, progressive damage, finite-element analysis, notches, open hole, strength, failure mechanisms


    Author Information:

    Bau, H
    President and vice president, NSE Composites Stress Services, Seattle, WA

    Hoyt, DM
    President and vice president, NSE Composites Stress Services, Seattle, WA

    Rousseau, CQ
    Principal engineer, Research Structures, Bell Helicopter Textron, Fort Worth, TX


    Paper ID: STP14514S

    Committee/Subcommittee: D30.05

    DOI: 10.1520/STP14514S


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