The objective of this work was to investigate the compressive failure response of composite sandwich structures of four different configuration designed to produce different failure modes. Specimens were tested with no damage, with 0.25- inch-diameter open holes, and with three levels of impact damage. The facesheets consisted of two, three, or four layers of carbon/epoxy plain-weave fabric. Nomex and aluminum honeycomb were used as core materials. Strain gages were used to monitor the in-place strain distribution around the damaged area.
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