Fatigue of foam core sandwich beams—2: effect of initial damage

Burman, Magnus; Zenkert, Dan

doi:10.1016/s0142-1123(97)00068-6

Cited by 85 publications

(49 citation statements)

References 6 publications

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“…Both interface debonds and flawed butt-joints were also tested in fatigue load using the same type of material configurations and test set-up [15,16]. In a similar study [17] also beam configurations with honeycomb cores were tested in fatigue.…”

Section: Disbonds In Sandwich Beamsmentioning

confidence: 99%

Damage Tolerance of Naval Sandwich Panels

Zenkert

2009

Major Accomplishments in Composite Materials and Sandwich Structures

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This paper is a review of activities concerning various damage tolerance modelling and testing aspects of sandwich panels for typical Naval applications. It starts with a review of testing methods for primarily core materials and how to extract properties and data required for damage tolerance assessment. Next some typical damage types are defined and how they are modelled with the aim of predicting their effect on load bearing capacity. The paper then describes in brief how such models can used in the context of providing a systematic damage assessment scheme for composite sandwich ship structures.

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Section: Disbonds In Sandwich Beamsmentioning

confidence: 99%

Damage Tolerance of Naval Sandwich Panels

Zenkert

2009

Major Accomplishments in Composite Materials and Sandwich Structures

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“…A good summary of what has been done can be found in [1]. Some early work was performed by Burman et al [2][3], Shenoi et al [4], Buene et al [5] and Kanny and Mahfuz [6]. Kanny and Mahfuz [7] and Kulkarni et al [8] performed fatigue testing of foam core sandwich beams with polymer foam cores.…”

Section: Introductionmentioning

confidence: 99%

Tension, compression and shear fatigue of a closed cell polymer foam

Zenkert

Burman

2009

Composites Science and Technology

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PostprintThis is the accepted version of a paper published in Composites Science And Technology. This paper has been peer-reviewed but does not include the final publisher proof-corrections or journal pagination. AbstractA closed cell foam of Polymetacrylimide (Rohacell) with three different densities is studied.The foam is tested quasistatically in tension, compression and shear. The tensile properties scale very well with the relative density of the foam, but the compression and shear properties do not scale the same way. It is believed to be due to cell edge and cell wall buckling being the dominated deformation mechanism in compression and shear for lower densities that does not occur for higher densities. Fatigue testing is then performed in tension, compression and shear. It is seen that for all load cases and densities, the fatigue life can be plotted using Basquin's law. The results also show that the different failure mechanisms found in the static tests are the same in fatigue. This means that the fatigue life for different load types exhibit different failure mechanisms. This shows not only as a clear difference in the stress levels for fatigue failure, but also on the slope in the fatigue life relation.

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“…Their situation was similar to this report in that the damaged area was small relative to either the width or length of the structure. In contrast, Burman and Zenkert (1997) found reduced fatigue performance for plates with manufactured core/skin disbonds. While it is not stated in their report, we suspect that the manufactured disbonds spanned the width of the specimens.…”

Section: Introduction Tmentioning

confidence: 88%

The Influence of Low Energy Impacts on the Static and Dynamic Response of a Foam Core Composite Wing

Aktaş

Seaver

Nichols

et al. 2009

Journal of Intelligent Material Systems and Structures

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This work describes damage detection efforts on a composite wing subject to a series of low-energy ($7 J) impacts. Two airfoils with fundamentally different damage scenarios were considered. The first damage scenario produced no visible signs of damage on the wing surface following eight impacts. A duplicate wing, subjected to a similar series of impacts, was investigated using flash thermography and subsequently autopsied. The flash thermography showed small, localized damage in the skin, but gave no information about core damage. The autopsy showed core/skin disbonding at both interfaces that varied with the number of impacts, core crushing, and a through the core shear crack. No clear changes to the static or dynamic wing response were observed for this scenario. The second damage scenario involved cracking of the wing skin. While damage quantification was not undertaken for this scenario, both static and dynamic changes in wing response were observed. An analytical model of the wing is presented which helps explain the observed behaviors of the two damage scenarios.

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Fatigue of foam core sandwich beams—2: effect of initial damage

Cited by 85 publications

References 6 publications

Damage Tolerance of Naval Sandwich Panels

Damage Tolerance of Naval Sandwich Panels

Tension, compression and shear fatigue of a closed cell polymer foam

The Influence of Low Energy Impacts on the Static and Dynamic Response of a Foam Core Composite Wing

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