Evaluating the Characteristics of Sandwich Composite Structures under Quasi-Static Loading

Abstract

The integrity of composite structures used in aircraft is crucial and is regularly a subject of discussion. Sandwich composite panels with carbon fibre reinforced laminate skin and flax fibre reinforced laminate skin; both with hemp as the core material were subjected static loading test of 10 mm/min indenter speed. The carbon fibre skin panels were more tolerant to the loading, but the flax fibre skin panels although with lower peak load did not show interlaminar failure like delamination in the response.