Composite plates under compression and/or shear loading are sensitive to buckling failures. A typical situation where a stiffened composite plate has buckled between the stiffeners is shown in this chapter. The skin—stiffener separation mode is fairly common in post‐buckled stiffened panels and may lead to premature failure. Depending on the application, designing for buckling and using any post‐buckling capability as an extra degree of conservatism is one of the possible approaches. Even in post‐buckled panels, accurate calculation of the buckling load for different loading combinations and boundary conditions is paramount in the design. In this chapter, buckling equations for a rectangular composite plate under biaxial loading, uniaxial compression, shear, and combined loads are derived.


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    Titel :

    Buckling of Composite Plates


    Beteiligte:


    Erscheinungsdatum :

    17.05.2013


    Format / Umfang :

    28 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Buckling of Composite Plates

    Kassapoglou, Christos | Wiley | 2010


    Pulse buckling of composite plates

    Ari-Gur, Judah / Simonetta, Samuel | AIAA | 1994


    Secondary buckling of laminated composite plates

    Tiwari, Nachiketa / Hyer, Michael | AIAA | 2000


    Buckling of Laminated Composite Rectangular Plates

    Shukla, K.K. | Online Contents | 2005


    Secondary Buckling of Laminated Composite Plates

    Hyer, M. W. / Tiwari, N. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 2000