STP617

    Structural Design Significance of Tension-Tension Fatigue Data on Composites

    Published: Jan 1977


      Format Pages Price  
    PDF Version (200K) 14 $25   ADD TO CART
    Complete Source PDF (8.2M) 14 $165   ADD TO CART


    Abstract

    Constant cycle tension-tension fatigue and related static tension data have been generated on six single composite material/orientation combinations and twenty-one hybrid composite material/orientation combinations. Anomalies are related to the temperature rise and stopped interval creep, whereas endurance limit stresses (runouts) are associated with static proportional limit values, when they occur, and internal damage. The significance of these room temperature-dry data on the design allowables and weight of aerodynamic structures is discussed. Such structures are helicopter rotor blades and wing and horizontal stabilizer lower surfaces. Typical criteria for turning these data into preliminary allowables are shown, as are examples of such allowables developed from the data. These values are then compared to those that might be used if the structures were made of metal.

    Keywords:

    composite materials, fatigue (materials), stress strain diagrams, design allowables, polymers, structures, aircraft, helicopters, endurance limit


    Author Information:

    Grimes, GC
    Engineering specialist, Northrop Aircraft Co., Hawthorne, Calif


    Paper ID: STP26938S

    Committee/Subcommittee: D30.05

    DOI: 10.1520/STP26938S


    CrossRef ASTM International is a member of CrossRef.