Volume 4, Issue 4 (December 1982)

    Three-Dimensional Analysis of [0/90]s and [90/0]s Laminates with a Central Circular Hole

    CODEN: CTROAD

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    Abstract

    Stress distributions were calculated near a circular hole in [0/90]s and [90/0]s laminates, using a three-dimensional finite-element analysis. These stress distributions were presented in three ways: through the thickness at the hole boundary, along radial lines at the 0/90 and 90/0 interfaces, and around the hole at these interfaces. The interlaminar normal stress σz and the shear stress σ distributions had very steep gradients near the hole boundary, which suggested interlaminar stress singularities. The largest compressive σz stress occurred at about 60° from the load axis; the largest σ occurred at about 75°. A simple procedure was introduced to calculate interlaminar stresses near the hole boundary. It used strains calculated by an exact two-dimensional analysis of a laminate with a hole as input to a quasi-three-dimensional model. It produced stresses that closely agreed with those from the three-dimensional finite-element model. For laminates with holes, this simple procedure may become a viable alternative to three-dimensional finite-element analyses.


    Author Information:

    Raju, IS
    Associate research professor and senior engineer, Joint Institute for Advancement of Flight Sciences, George Washington University, School of Engineering and Applied Science, NASA Langley Research Center, Hampton, VA

    Crews, JH
    Associate research professor and senior engineer, Joint Institute for Advancement of Flight Sciences, George Washington University, School of Engineering and Applied Science, NASA Langley Research Center, Hampton, VA


    Stock #: CTR10773J

    ISSN: 0884-6804

    DOI: 10.1520/CTR10773J

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    Author
    Title Three-Dimensional Analysis of [0/90]s and [90/0]s Laminates with a Central Circular Hole
    Symposium , 0000-00-00
    Committee D30