STP893

    Improvement of Edge Delamination Strength of Composite Laminates Using Adhesive Layers

    Published: Jan 1986


      Format Pages Price  
    PDF (480K) 20 $25   ADD TO CART
    Complete Source PDF (8.9M) 20 $65   ADD TO CART


    Abstract

    A thin but tough adhesive inner layer placed in laminates at the proper interface has been found to give improved delamination strength. Static tension tests of laminates with (±302/˙903/∓302)T and (±35/0/90)s layups of graphite/epoxy show that the added adhesive inner layer effectively suppresses delamination until final failure. The effects of adhesive layers on interlaminar stresses and strain-energy release rate have been studied analytically using a finite-element method. It was found that the introduction of adhesive layers reduced the interlaminar stresses. Although there was no significant change in total strain-energy release rate, there was a significant decrease in the G1 (tension mode) percentage of the total strain-energy release rate.

    Keywords:

    edge delamination, interlaminar stress, strain-energy release rate, adhesive layer, graphite/epoxy, composite materials, damage tolerance, interlaminar fracture toughness


    Author Information:

    Chan, WS
    Senior engineering specialist, Research Group; chief of LHX Airframe and Stress; and former staff member, Research Group, Bell Helicopter Textron Inc., Fort Worth, TX

    Rogers, C
    Senior engineering specialist, Research Group; chief of LHX Airframe and Stress; and former staff member, Research Group, Bell Helicopter Textron Inc., Fort Worth, TX

    Aker, S
    Senior engineering specialist, Research Group; chief of LHX Airframe and Stress; and former staff member, Research Group, Bell Helicopter Textron Inc., Fort Worth, TX


    Paper ID: STP35353S

    Committee/Subcommittee: D30.06

    DOI: 10.1520/STP35353S


    CrossRef ASTM International is a member of CrossRef.