Abstract
This paper presents an experimental study which examines the tensile and compressive response of a quasi-isotropic carbon fibre reinforced polymer (CFRP) laminate subjected to ambient conditions and environmental extremes associated with aircraft design. Specimens with and without holes are considered within the context of structural features and associated design allowables. The data obtained, relating to the effect of sample replicates and specimen geometry on the variability in failure strength, support the concept of a reduced qualification test programme for CFRP.
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