Certification and damage tolerance criteria are critical technologies for the advancement of composites structures on commercial aircraft. Understanding and predicting the path and propagation load of crack-like damage in these anisotropic structures is necessary to meet certain requirements. Under the NASA High Speed Research program, the behavior of these cracks were investigated using honeycomb core-stiffened curved panels. The work was complimented by previous work using flat laminated panels. The panels were designed with integral straps that contained a majority of the 0 degree plies in the laminate. The difference in stiffness of the base panel and tear strap region was designed to change the direction of crack propagation. The panels were tested under combined loads typical of those experienced on an aircraft. Finite element analysis was used to predict the strain distribution around the crack tip. The cracks were analyzed as ideal cracks and the strain around the crack was interrogated in an R-theta coordinate system. The method developed facilitated prediction of the direction that the crack would propagate and the initial failure load. The cracks in both panels propagated as predicted.


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    Titel :

    Propagation and control of crack-like damage in curved composite panels under combined loads


    Beteiligte:
    Mahler, M. (Autor:in) / Ley, R. (Autor:in) / Shah, C. (Autor:in) / Lin, Weichuan (Autor:in) / Rouse, M. (Autor:in)


    Erscheinungsdatum :

    2000


    Format / Umfang :

    9 Seiten, 5 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Propagation and control of crack-like damage in curved composite panels under combined loads

    Mahler, Mary / Ley, Robert / Shah, Chandu et al. | AIAA | 2000


    Propagation and Control of Crack-Like Damage in Curved Composite Combined Loads

    Ley, R. P. / Lin, W. / Mahler, M. A. et al. | British Library Conference Proceedings | 2000