Experimental Investigation of Static and Fatigue Behavior of Honeycomb Cores Under In-Plane Shear Loads

Bianchi, Gabriel; Aglietti, Guglielmo S.; Richardson, Guy

doi:10.2514/6.2009-2674

Cited by 1 publication

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“…This highlights the need for further investigations in this area. Furthermore, apart from an early work from the present authors [10], there are no works which consider the behavior of honeycomb cores under in-plane shear dynamic loads. The variation of static core shear strength and shear modulus is another area which has not been investigated in the literature.…”

Section: Introductionmentioning

confidence: 96%

Static and Fatigue Behaviour of Hexagonal Honeycomb Cores under In-plane Shear Loads

2011

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Due to their high specific strength and high specific stiffness properties the use of honeycomb panels is particularly attractive in spacecraft structures. However, the harsh environment produced during the launch of a satellite can subject the honeycomb cores of these sandwich structures to severe quasi-static and dynamic loads, potentially leading to static or early fatigue failures. Knowledge of the static and fatigue behavior of these honeycomb cores is thus a key requirement when considering their use in spacecraft structural applications. This paper presents the findings of an experimental test campaign carried out to investigate the static and fatigue behaviors of aluminum hexagonal honeycomb cores subject to in-plane shear loads. The investigation involved carrying out both static and fatigue tests using the single block shear test method. These results are also discussed in relation to the observed damage and failure modes which have been reported for the statically tested specimens and for the fatigue tested specimens at various stages of fatigue life. As well as conducting tests for the more conventional principal cell orientations (L and W), results are also presented for tests carried out at intermediate orientations to investigate the variation of core shear strength with loading orientation. The results are further investigated using explicit non-linear finite element analysis to model the buckling failure mechanisms of the tested cores.

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Section: Introductionmentioning

confidence: 96%