22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-4.1.R1

INFLUENCE OF CONTACT PHENOMENA ON EMBEDDED DELAMINATIONS GROWTH IN COMPOSITE

A. Riccio (1), F. Scaramuzzino (2), P. Perugini (2)
(1) Department of Aerospace Engineering, 2nd University of Naples, ITALY; (2) C.I.R.A. (Italian Aerospace Research Centre), ITALY

Keywords: buckling, delamination growth, contact, composites

In this paper, numerical geometrically non-linear analyses have been performed to investigate the influence of contact phenomena on multiple embedded delaminations growth in composite panels under compressive load. An in-house FEM code based on the Modified Virtual Crack Closure Technique to analyse delaminations growth and with the Penalty Method Approach to take into account contact phenomena has been used for computations. Compressed composite panels with two embedded delaminations has been investigated for various geometrical configurations with different delaminations’ sizes and positions. Comparisons with a single embedded delamination model adopted in previous works have been presented. Finally a comparison between contact and no-contact approaches has been shown for a significant geometrical configuration.

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