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This and the next slide are from:
G.A. Kardomateas (School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, Georgia, USA), “Snap buckling of delaminated composites under pure bending”, Composites Science and Technology, Vol. 39, pp 63-74, 1990
ABSTRACT: Delaminated composites under pure bending can undergo snap buckling under certain conditions of applied bending load and geometrical configuration. The phenomenon is demonstrated experimentally and is investigated theoretically by an energy procedure. The geometric non-linearities are intluded in the formulation. First, a theoretical analysis is performed to model the behavior of the system and define the conditions for snap buckling. The predicted buckling loads are then compared with experimentally obtained data from pure bending loading of Kevlar epoxy specimens with internal delaminations. Good agreement is obtained betlreen the experimental and theoretical results.
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