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Sandwich-structured composite

About: Sandwich-structured composite is a research topic. Over the lifetime, 5853 publications have been published within this topic receiving 101126 citations.


Papers
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Journal ArticleDOI
TL;DR: In this article, failure modes of different sandwich panels were analyzed by observing the contact surface and the cross section through damage region, and the microstructure of the impacted specimens was carried out.

88 citations

Journal ArticleDOI
TL;DR: In this article, an integrated hollow (space) E-glass/epoxy core sandwich composite construction that possesses several multi-functional benefits in addition to the providing lightweight and bending stiffness advantages was investigated.
Abstract: This paper deals with an innovative integrated hollow (space) E-glass/epoxy core sandwich composite construction that possesses several multi-functional benefits in addition to the providing lightweight and bending stiffness advantages. In comparison with traditional foam and honeycomb cores, the integrated space core provides a means to route wires/rods, embed electronic assemblies, and store fuel and fire-retardant foam, among other conceivable benefits. In the current work, the low-velocity impact (LVI) response of innovative integrated sandwich core composites was investigated. Three thicknesses of integrated and functionality-embedded E-glass/epoxy sandwich cores were considered in this study—including 6, 9 and 17 mm. The low-velocity impact results indicated that the hollow and functionality-embedded integrated core suffered a localized damage state limited to a system of core members in the vicinity of the impact. The peak forces attained under static compression and LVI were in accordance with Euler's column buckling equation. Stacking of the core was an effective way of improving functionality and limiting the LVI damage in the sandwich plate. The functionality-embedded cores provided enhanced LVI resistance due to energy additional energy absorption mechanisms.

88 citations

Journal ArticleDOI
TL;DR: In this article, the problem of local bending in sandwich panels with a soft core was investigated by conducting a series of photoelastic experiments, and the experimental results were compared with analytical results obtained using the high-order sandwich panel theory (HSAPT).

88 citations

Journal ArticleDOI
TL;DR: In this paper, the structural response of composite panels with triple layered graded honeycomb cores under blast loading was analyzed by using finite element software LS-DYNA after validation against the experiments and the structural deformation modes were classified into three types and the core layer deformation was divided into three regions.

88 citations

Journal ArticleDOI
TL;DR: In this article, the stiffness matrices corresponding to these sinusoidal edge loads are derived, taking account of the destabilising effect of the basic longitudinal compressive stress, not only in the out-of-plane but also in the in-plane deformations.
Abstract: This paper provides the basis for a very general approach to the determination of initial buckling stresses of long stiffened panels in uniform longitudinal compression. The panels are assumed to consist of a series of long flat strips, rigidly connected together at their edges, as in panels with top-hat or Z-section stringers, or in sandwich panels with corrugated cores. Whatever the buckling mode, the individual flats are subjected, just after buckling, to sinusoidally varying systems of both out-of-plane and in-plane edge forces and moments, superimposed on the basic state of uniform compression. The stiffness matrices corresponding to these sinusoidal edge loads are derived, taking account of the destabilising effect of the basic longitudinal compressive stress, not only in the out-of-plane but also in the in-plane deformations. For the latter purpose a non-linear theory of elasticity is used. The application of these stiffness matrices to specific panels is briefly described. All possible modes are incorporated within one determinantal equation. For panels with identical stiffeners spaced at equal intervals, the order of the determinant is independent of the number of stiffeners.

88 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
2023194
2022402
2021298
2020299
2019273
2018271