Local buckling on large sandwich panels used in light aviation: Experimental setup and failure scenarios

The design of light aircraft sandwich structures is driven by a local buckling phenomenon named “wrinkling” which can be the primary cause failure such structures. Structural tests using VERTEX methodology were performed to access wrinkling behaviour 558x536 mm 2 technological specimens representative used in aviation. operating principle machine use four hydraulic actuators load rectangular box structure, upper part central being closed under test. Thus, tested compressive and shear loading. A scenario was identified thanks Stereo Digital Image Correlation high-speed camera. Wrinkling localisation mechanical geometrical aspects. Experiments on panels remain rare literature at this level test pyramid for certification aeronautical This scale presents some advantages as it allows multiaxial loading boundary conditions consistent with lightweight structure. Technological elements also added study their influence result will lead interesting future investigations dialogue between experiments models forthcoming paper.