You are being redirected because this document is part of your ASTM Compass® subscription.
    This document is part of your ASTM Compass® subscription.


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

    Published: 0

      Format Pages Price  
    PDF (412K) 20 $25   ADD TO CART
    Complete Source PDF (15M) 549 $325   ADD TO CART

    Cite this document

    X Add email address send
      .RIS For RefWorks, EndNote, ProCite, Reference Manager, Zoteo, and many others.   .DOCX For Microsoft Word


    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.


    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

    Committee/Subcommittee: D30.05

    DOI: 10.1520/STP14514S