The influence of a tension load on the behavior of laminates subjected to torsion was evaluated through test and analysis. Nine different 32-ply glass-epoxy laminates, typical of flexbeams in helicopter rotor systems, were tested under torsion and combined tension-torsion. The laminate configurations consisted of 30 45 or 60 deg of angle plies located between 0 deg of angle sublaminates. Superposing a tension load increased both the torsional load required to twist to a given angle and the torsional load to failure. An increase in the torsional load for a given twist increases the control load to the helicopter rotor system. All failures initiated with through-the-thickness shear cracks at the free edge, followed by deliminations. The failure locations depended on the load and the laminate configuration. The laminate layups are compared to determine the design efficiency with respect to the control loads required for, and the residual strength remaining following, a given twist angle.


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    Title :

    The influence of a tension load on laminates under torsion


    Additional title:

    Der Einfluß einer Zugbelastung auf das Werkstoffverhalten von Laminaten unter Torsion im Hinblick auf deren Verwendung für Hubschrauber-Rotorblätter


    Contributors:
    Sen, J.K. (author)


    Publication date :

    1994


    Size :

    11 Seiten, 14 Bilder, 12 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    The Influence of Tension Load on Laminates under Torsion

    Sen, J. K. / American Helicopter Society | British Library Conference Proceedings | 1994





    COMPOSITE TENSION-TORSION LOAD CELL

    Agarwal, S. / Kim, I. B. / Dancila, D. S. et al. | British Library Conference Proceedings | 2003