The local buckling and the associated postbuckling response of stiffened composite shells are studied using an asymptotic approach. Both the classical (Kirchhoff) theory (CPT) and a first-order shear deformation theory (SDT) are employed in the study. SDT analysis was carried out using p-version type finite strips, whereas CPT analysis employed h-version based strips. Convergence studies confirm the superiority of the p-version approach. A panel width-to-thickness ratio of 50 was chosen to investigate the influence of shear deformation for stiffened and isolated panels fabricated out of isotropic and composite layered materials. The shear deformation effects were significant for composite stiffened shell panels with CPT giving a noticeably stiffer response. In comparison with isotropic shell panels, orthotropic layered panels buckle at lower nondimensional buckling loads but are appreciably less sensitive to imperfection.


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    Titel :

    Postbuckling response of stiffened composite cylindrical shells


    Beteiligte:

    Erschienen in:

    AIAA Journal ; 30 , 12


    Erscheinungsdatum :

    1992-12-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Postbuckling response of stiffened composite cylindrical shells

    SRIDHARAN, SRINASAN / ZEGGANE, MADJID / STARNES, JAMES H. | AIAA | 1992



    Delanination Buckling and Postbuckling of Composite Cylindrical Shells

    Gu, H. / Chattopadhyay, A. / American Institute of Aeronautics and Astronautics| ASME| ASCE | British Library Conference Proceedings | 1995



    Delamination buckling and postbuckling of composite cylindrical shells

    Gu, Haozhong / Chattopadhyay, Aditi | AIAA | 1996