TY - JOUR
AU - Dattaguru, B.
AB - Fibre-reinforced polymer laminated composites have found extensive applications in the aviation industry due to their exceptional properties and advantages over other materials. But when interface becomes weaker in the transverse direction due to manufacturing defects or impact loads or other processing activities, among the failure mechanisms de-laminations could occur and these are known to degrade the buckling strength of the laminated composite structures under compressive loads. Failure in typical delamination configurations are studied in the current work under progressively increasing compressive loads using cohesive zone modelling. To initiate the current work, the size effects of de-laminations are investigated followed by the size of the insert that produces delamination damage during fabrication. In the analysis, through mode I strain energy release rates (SERR), the load to initiate delamination is estimated. Both buckling and post-buckling regimes are studied. Apart from these models, a composite panel (NASA Panel), on which experimental work was reported in the literature, is analysed for comparison purposes. In addition, a cross-ply laminate is analysed using surface-based cohesive contact method and the solution is compared with results obtained for the same problem using MVCCI post-processing technique for different imperfection factors. The focus of this paper will be on inter-laminar delamination.
TI - Study of circular embedded delamination in laminated composites by prognostic approach for structural health monitoring applications
JF - ISSS Journal of Micro and Smart Systems
DO - 10.1007/s41683-022-00105-9
DA - 2022-11-01
UR - https://www.deepdyve.com/lp/springer-journals/study-of-circular-embedded-delamination-in-laminated-composites-by-v0iZhD7VEn
SP - 383
EP - 396
VL - 11
IS - 2
DP - DeepDyve
ER -