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Sandwich panel

About: Sandwich panel is a research topic. Over the lifetime, 4665 publications have been published within this topic receiving 49812 citations.


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Patent
21 Aug 1978
TL;DR: In this article, a weather-proof attachment device was proposed to connect sandwich panel wall system modules to concrete floors including a bracket under the wall with an upright rail connected to the inside facia sheet of the sandwich panel and an outside inverted U-shape rail extending into the interior core of the panel, the groove to receive the edge of a protection sheet from below extending from the bracket across the surface of the concrete and over the corner of the slab.
Abstract: A weather proof attachment device to connect sandwich panel wall system modules to concrete floors including a bracket under the wall with an upright rail connected to the inside facia sheet of the sandwich panel and an outside inverted U-shape rail extending into the interior core of the panel, the groove to receive the edge of a protection sheet from below extending from the bracket across the surface of the concrete and over the corner of the slab to prevent weather and rain from entering therein.

33 citations

Journal ArticleDOI
TL;DR: In this paper, the lattice truss structures (LTS) are used for 3D-printing of sandwich panels and the absorption energy and failure mechanisms of lattice cells under low-velocity impact loads are investigated.
Abstract: Sandwich panel structures are widely used in aerospace, marine, and automotive applications because of their high flexural stiffness, strength-to-weight ratio, good vibration damping, and low through-thickness thermal conductivity. These structures consist of solid face sheets and low-density cellular core structures, which are traditionally based upon honeycomb folded-sheet topologies. The recent advances in additive manufacturing (AM) or 3D printing process allow lattice core configurations to be designed with improved mechanical properties. In this work, the sandwich core is comprised of lattice truss structures (LTS). Two different LTS designs are 3D-printed using acrylonitrile butadiene styrene (ABS) and are tested under low-velocity impact loads. The absorption energy and the failure mechanisms of lattice cells under such loads are investigated. The differences in energy-absorption capabilities are captured by integrating the load–displacement curve found from the impact response. It is observed that selective placement of vertical support struts in the unit-cell results in an increase in the absorption energy of the sandwich panels.

33 citations

Journal ArticleDOI
TL;DR: In this paper, an equivalent plate model was proposed to analyze the mechanical behavior of corrugated-core sandwich panels under tensile and bending loads, which can be easily obtained by combining the equivalent energy method and the classical lamination theory.
Abstract: This paper suggests an equivalent plate model to analyze the mechanical behavior of corrugated-core sandwich panels under tensile and bending loads. A homogenization-based theory based on the equivalent energy method is used to obtain the stiffness matrices of corrugated cores of a sandwich panel. Equivalent continuum layers with orthotropic elastic constants corresponding to the membrane and bending stiffness terms of the corrugated layers are determined by using classical lamination theory (CLT). The importance of this work is that an equivalent plate model for corrugated-core sandwich panels can be easily obtained by combining the equivalent energy method and the CLT. The proposed equivalent model is verified by numerical simulations of sandwich panels with sinusoidal and trapezoidal corrugated cores.

33 citations

Proceedings ArticleDOI
01 Apr 2005
TL;DR: In this paper, a set of composite sandwich panels and cross-ribbed panels were analyzed and the optimal values of rib and skin thickness, rib spacing, and panel depth were obtained for minimal weight under stress and buckling constraints.
Abstract: Structural analysis and design of efficient pressurized fuselage configurations for the advanced Blended-Wing-Body (BWB) flight vehicle is a challenging problem. Unlike a conventional cylindrical pressurized fuselage, stress level in a box type BWB fuselage is an order of magnitude higher, because internal pressure primarily results in bending stress instead of skin-membrane stress. In addition, resulting deformation of aerodynamic surface could significantly affect performance advantages provided by lifting body. The pressurized composite conformal multi-lobe tanks of X-33 type space vehicle also suffered from similar problem. In the earlier BWB design studies, Vaulted Ribbed Shell (VLRS), Flat Ribbed Shell (FRS); Vaulted shell Honeycomb Core (VLHC) and Flat sandwich shell Honeycomb Core (FLHC) concepts were studied. The flat and vaulted ribbed shell concepts were found most efficient. In a recent study, a set of composite sandwich panel and cross-ribbed panel were analyzed. Optimal values of rib and skin thickness, rib spacing, and panel depth were obtained for minimal weight under stress and buckling constraints. In addition, a set of efficient multi-bubble fuselage (MBF) configuration concept was developed. The special geometric configuration of this concept allows for balancing internal cabin pressure load efficiently, through membrane stress in inner-stiffened shell and inter-cabin walls, while the outer-ribbed shell prevents buckling due to external resultant compressive loads. The initial results from these approximate finite element analyses indicate progressively lower maximum stresses and deflections compared to the earlier study. However, a relative comparison of the FEM weight per unit floor area of the segment unit indicates that the unit weights are still relatively higher that the conventional B777 type cylindrical or A380 type elliptic fuselage design. Due to the manufacturing concern associated with multi-bubble fuselage, a Y braced box-type fuselage alternative with special resin-film injected (RFI) stitched carbon composite with foam-core was designed by Boeing under a NASA research contract for the 480 passenger version. It is shown that this configuration can be improved to a modified multi-bubble fuselage which has better stress distribution, for same material and dimension.

33 citations

Journal ArticleDOI
01 Jan 2008
TL;DR: In this article, a multi-functional structure based on the secondary power system is proposed to save mass from a spacecraft by incorporating other functional subsystems into the structure, and the feasibility of the proposed multifunction structure is demonstrated though vibration testing on a single cell and successful manufacture of a test panel.
Abstract: A multi-functional structure saves mass from a spacecraft by incorporating other functional subsystems into the structure. By using the structural properties of a non-structural element, inert structure may be eliminated, and the requirement to allot internal volume to the subsystem in question is removed. The current paper describes a multi-functional structure based on the secondary power system. By using commercially available plastic lithium-ion cells to form the core of a sandwich panel, inert mass is eliminated from both the structure and from the battery enclosure. The feasibility of the proposed multi-functional structure is demonstrated though vibration testing on a single cell, and the successful manufacture of a test panel. The work goes on to quantify the potential mass savings that may be achieved by using a multi-functional structure of this type. By varying a set of spacecraft attributes, the study identifies that small spacecraft with high power requirements have the potential to gain the most benefit from using a multi-functional structure of this type. © IMechE 2008.

33 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202384
2022217
2021244
2020280
2019264
2018252