Behavior of flat panels with honeycomb filler in the presence of internal defects of various shapes


Аuthors

Rabinsky L. N., Martirosov M. I., Dedova D. V.*

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: darina.dedova98@gmail.com

Abstract

The article investigates the behavior of flat three-layer panels with honeycomb core in the presence of internal defects of the delamination type of various shapes. This paper discusses round and elliptical shape defects that may occur during manufacturing or operational processes. The study examines the impact of dynamic loads, including impacts from an absolutely rigid striker and fragments of reinforced rubber, simulating the rupture of an aircraft tire. The finite element method was used to determine stress fields and the distribution of failure indices. The finite element model is made in the LS-DYNA frame complex. The research evaluates the mechanical response of panels made from different materials, specifically glass-reinforced honeycomb (SSP-1-2.5) and polymer-reinforced honeycomb (PSP-1-2.5-144), under both defective and defect-free conditions. The results reveal that the presence of defects significantly increases stress concentrations in the panels, with stresses in SSP-1-2.5 panels being 3% higher compared to PSP-1-2.5-144 panels. The failure indices, calculated using the LaRC04 (Langley Research Center) criterion for polymer composite materials (PCM), exceed unity in panels with defects, indicating the onset of failure in the upper cladding layer. In contrast, panels without defects exhibit no signs of failure, with stress levels being five times lower than in defective panels. Additionally, the study compares the behavior of panels with multiple elliptical defects, showing that stresses in PSP-1-2.5-144 panels are 11% higher than in SSP-1-2.5 panels under similar conditions. The research also highlights the dynamic response of the panels, including the rebound of rubber fragments and the displacement of the cladding layers.

Keywords:

finite element method, three-layer panels, honeycomb filler, defects, failure criteria, composite materials

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