Strain energy release rate analysis of delamination in a tapered laminate subjected to tension loadFinite element method was used to analyze a tapered glass/epoxy composite laminate subjected to a tension load, in order to determine the interlaminar stress distributions the strain-energy release rate for the delamination growth that may occur due to ply drops. In a laminate having a typical configuration of a helicopter hub, the (+/- 45)3 plies were dropped in three distinct steps, each 20-ply thickness apart, with the resulting taper angle of 5.71 deg. Delaminations were assumed to initiate at the bottom of the taper on the -45/+45 interface, and the delamination growth was simulated along the taper and into the thin region. The results of the analysis indicated that a delamination initiating at the end of the taper will grow unstably along the taper and the thin laminate simultaneously.
Document ID
19890043237
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Salpekar, S. A. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Raju, I. S. (Analytical Services and Materials, Inc. Hampton, VA, United States)
O'Brien, T. K. (NASA Langley Research Center; U.S. Army, Aerostructures Directorate, Hampton VA, United States)