A study of fastener pull-through failure of composite laminates. Part 1. Experimental

Of the extensive number of investigations examining mechanically fastened c omposite joints, all but a few are limited to consideration of in-plane mod es of failure. An experimental and numerical investigation of fastener pull -through failure of composite joints has therefore been undertaken. The exp erimental program included an investigation of the influence fastener head geometry, laminate thickness, stacking sequence and material system have up on the pull-through loading response. Circular specimens were transversely loaded to pre-determined displacements of the fastener, sections through th e specimen taken and their failure mechanisms investigated with an optical microscope. Pull-through failure was found to be characterised by substanti al interval damage similar to that observed for low-velocity impacted compo site panels. Failure is not evident from inspection of the laminate surface s. Damage is manifested in the form of a conically distributed network of m atrix cracking and delaminations extending through-the-thickness from the f astener head outer edge, directed away from the fastener hole. The internal /barely visible nature of failure represents a significant departure from t hat generally considered to distinguish fastener pull-through failure. The means by which to increase resistance to pull-through failure are discussed . This research constitutes work performed as part of the Cooperative Resea rch Centre for Advanced Composite Structures (CRC-ACS) task on highly loade d joints. (C) 1999 Elsevier Science Ltd. All rights reserved.