Experimental failure investigation of pull-off tests of single T-stiffened composite specimens

Published on Oct 1, 2017in Composite Structures5.407
· DOI :10.1016/J.COMPSTRUCT.2017.04.070
J. Justo7
Estimated H-index: 7
(University of Seville),
José Reinoso22
Estimated H-index: 22
(University of Seville),
Antonio Blázquez19
Estimated H-index: 19
(University of Seville)
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Abstract
Abstract This paper investigates the initiation and progression of interlaminar failure complying with characteristic postbuckling deformation patterns using single T-joint specimens with different geometric definitions and laminate disposals. The analysis herein conducted addresses the role of these aspects regarding the characteristic failure behavior in terms of: (i) damage initiation location, and (ii) progression path within the specimen. A thorough qualitative discussion concerning the damage initiation and subsequent progression path at the skin-stringer joint is supported by the development of a simple analytical model based on the Classical Laminate Theory denominated as 3-spot-joint model. These results provide a valuable insight into the principal mechanisms that govern such interlaminar damage events, which usually provoke the structural collapse in actual carbon fiber reinforced polymer composite stiffened panels.
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