Topic
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.
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TL;DR: In this paper, the authors provided the Bending-Gradient homogenization scheme and applied it to a sandwich panel including the chevron pattern, and found that the shear forces stiffness of the sandwich panel is strongly influenced by a skin distortion phenomenon.
57 citations
TL;DR: In this paper, the bending behavior of a curved sandwich panel with a transversely flexible core is derived using a rigorous systematic closed-form approach based on variational principles, and the effects of the transversely-flexible core are incorporated resulting in non-linear patterns, denoted also as high-order effects, for the inplane and the transverse deformations through the height of the core.
Abstract: The bending behavior of a curved sandwich panel with a transversely flexible core, ie, "soft" in the out of plane direction is derived It is formulated using a rigorous systematic closed-form approach based on variational principles The effects of the transversely flexible core are incorporated resulting in non-linear patterns, denoted also as high-order effects, for the inplane and the transverse deformations through the height of the core The governing equations along with the associated boundary and continuity conditions for a general type of sandwich panel, ie, unidentical skins, composite laminated or metallic and a "soft" core are derived General type of boundary conditions, including spring conditions, as well as different conditions at upper and lower skins at the same section, are implemented and the effects of "stiff' edge inserts, denoted as global boundary conditions, along with the induced localized effects are considered Localized effects at support regions with or without edge stif
57 citations
TL;DR: In this paper, an analytical model that permits the computation of stiffnesses as well as interfacial stresses considering the skin effect for hexagonal honeycomb sandwich, subjected to in-plane and out-of-plane forces is presented.
57 citations
TL;DR: In this article, the effects of varying skin thickness, core density and type, indenter nose shape, and boundary conditions on the damage and energy absorbing characteristics of honeycomb sandwich panels were examined.
Abstract: Honeycomb sandwich panels of various skin thicknesses and core densities have been investigated under quasi-static loading in bending and indentation with both hemispherical (HS) and flat-ended (FE) indenters. Core crushing, top skin delamination, and top skin fracture are identified as major damage mechanisms. Their characteristics and energy-absorbing capabilities are established using load—displacement and load—strain curves and inspections of cross-sectioned specimens. The effects of varying skin thickness, core density and type, indenter nose shape, and boundary conditions on the damage and energy-absorbing characteristics are examined. The variation of the indenter nose shape is shown to induce a change in the damage mechanisms and have the most significant effect on energy absorption, especially for panels with relatively thicker skins. Increasing the skin thickness significantly increases not only the initial threshold and ultimate loads but also the absorbed energy (AE) of the panels. Increasing ...
57 citations
TL;DR: In this paper, a weighted elastomer ball is dropped from increasing heights onto rigidly supported panels until damage is detected, and a test developed to simulate the water impact (slamming) loading of sandwich boat structures is presented.
Abstract: This paper presents results from a test developed to simulate the water impact (slamming) loading of sandwich boat structures. A weighted elastomer ball is dropped from increasing heights onto rigidly supported panels until damage is detected. Results from this test indicate that honeycomb core sandwich panels, the most widely used material for racing yacht hulls, start to damage due to core crushing at impact energies around 550 J. Sandwich panels of the same areal weight and with the same carbon/epoxy facings but using a novel foam core reinforced in the thickness direction with pultruded carbon fibre pins, do not show signs of damage until above 1200 J impact energy. This suggests that these will offer significantly improved resistance to wave impact. Quasi-static test results cannot be used to predict impact resistance here as the crush strength of the pinned foam is more sensitive to loading rate than that of the honeycomb core.
57 citations