Abstract
The experimental investigation on the compressive properties of honeycomb sandwich composite panels was carried out in this paper. The local compressive specimens and global compressive specimens were manufactured for compressive experiment. The test fixture has been designed and manufactured to examine the compressive behavior of honeycomb sandwich panel. The results indicate that there is no buckling occurred in local compressive specimen skin during the whole compressive experiment. The average failure load of local compressive specimens is 106884 N. The local buckling increases with the loading until the global compressive specimens are unstable. The fracture positions locate along the horizontal line at the middle height of global compressive specimen, which is different from local compressive specimens. The average buckling load and failure load of global compressive specimen are 31850 N and 82282 N respectively.
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