The strength characteristics of aluminum honeycomb sandwich panels (original) (raw)
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Stress–Strain Assessment of Honeycomb Sandwich Panel Subjected to Uniaxial Compressive Load
Journal of Marine Science and Engineering
The ship hull structure is composed of plates and stiffened panels. Estimating the maximum load-carrying capacity, or the ultimate strength, of these structural components is fundamental. One of the main challenges nowadays is the implementation of new materials and technologies to enhance the structural integrity, economy, safety and environmentally friendly design of the ship’s hull structure. A new design solution may be represented by aluminium alloy honeycomb sandwich structures, both as plane panels or stiffened ones, which are characterised by excellent impact-absorption capabilities and a high stiffness-to-weight ratio. Still, their response to some conditions typical of ship structural design needs to be deeply investigated. Axial compressive loading is one of the most critical conditions that could impact the structural integrity of such light-weight solutions. Hence, the uniaxial compressive behaviour of aluminium honeycomb sandwich structures has to be deeply investigate...
Strength Analysis on Honeycomb Sandwich Panels of different Materials
2014
Aluminum sandwich construction has been recognized as a promising concept for structural design of light weight systems such as wings of aircraft. A sandwich construction, which consists of two thin facing layers separated by a thick core, offers various advantages for design of weight critical structure. Depending on the specific mission requirements of the structures, aluminum alloys, high tensile steels, titanium or composites are used as the material of facings skins. Several core shapes and material may be utilized in the construction of sandwich among them, it has been known that the aluminum honeycomb core has excellent properties with regard to weight savings and fabrication costs.This paper is theoretically calculate
Experimental Study on Static and Dynamic Response of Aluminum Honeycomb Sandwich Structures
Materials, 2022
Honeycomb aluminum structures are used in energy-absorbing constructions in military, automotive, aerospace and space industries. Especially, the protection against explosives in military vehicles is very important. The paper deals with the study of selected aluminum honeycomb sandwich materials subjected to static and dynamic compressive loading. The used equipment includes: static strength machine, drop hammer and Split Hopkinson Pressure Bar (SHPB). The results show the influence of applied strain rate on the strength properties, especially Plateau stress, of the tested material. In each of the discussed cases, an increase in the value of plateau stresses in the entire strain range was noted with an increase in the strain rate, with an average of 10 to 19%. This increase is mostly visible in the final phase of structure destruction, and considering the geometrical parameters of the samples, the plateau stress increase was about 0.3 MPa between samples with the smallest and larges...
The aim of the present paper is to study the bending behaviour of honeycomb sandwich structure made of aluminium alloy cores, through the four point bending tests. Effects of the variation in honeycomb core height and honeycomb sandwich panel skin are investigated. The honeycomb panels demonstrate an initial linear elastic behaviour which is followed by nonlinear elastic-plastic behaviour. Also the flexural behaviour of honeycomb sandwich structure was analyzed by finite element analysis. The honeycomb sandwich panel failure modes are reported and discussed.
Bending Behavior of Aluminum Honey Comb Sandwich Panels
2020
Aluminum sandwich construction has been recognized as a promising concept for structural design of light weight systems such as wings of aircraft. A sandwich construction, which consists of two thin facing layers separated by a thick core, offers various advantages for design of weight critical structure. Depending on the specific mission requirements of the structures, aluminum alloys, high tensile steels, titanium or composites are used as the material of facings skins. Several core shapes and material may be utilized in the construction of sandwich among them, it has been known that the aluminum honeycomb core has excellent properties with regard to weight savings and fabrication costs. This paper is theoretically calculate bending behavior, of sandwich panels and to compare the strength to weight ratios of Normal Aluminium rod(panel) and Aluminium Honey Comb Panel .
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2006
The experiments were designed and performed to find the material properties of honeycomb sandwich panels and to find the difference in properties between aluminium and of glass fibre facing honeycomb sandwich panels, so as to get a path for consideration of panel containing maximum stiffness to weight ratio which is the main idea behind material selection for a spacecraft/satellite structure. Flatwise and edgewise compressive tests were performed on aluminium and glass fibre facing honeycomb sandwich panels of different core thickness to investigate the out-of-plane and in-plane compressive strength. The strain energy and the critical stress were calculated in one of the compression mode. Another set of experiments was performed to find the lamination strength of bond used for joining facing and core of honeycomb sandwich panels. Again the tests were performed on both facing types of sandwich panels to check the difference in strength with the change in core thickness and facing typ...
Journal of King Saud University - Science, 2019
Sandwich structures with glass fiber face sheets and aluminum honeycomb core are investigated computationally and experimentally. A three point bending load arrangement is conducted to examine the static and fatigue performance of honeycomb sandwich panel. Under static loading, the load and displacement response is indicated in five phases. The decrease in fatigue life with load level was observed in approximately linear manner. The visual and Scanning Electron Microscopic (SEM) analysis were carried out to analyze the failure modes. For static and high amplitude fatigue load, the failure initiates due to face yielding, while for low fatigue load failure initiates as a result of delamination at core and skin interface. However, in all cases principle failure mode is indentation. The honeycomb sandwich structure was also modeled with commercially available finite element packages ANSYS and the fatigue analyses were carried out to determine the life of specimens under load-displacement response. The experimental results were in good agreement with the Finite Element Analysis (FEA) results in both static and fatigue loads, and fracture modes prediction.
Mechanical characterization and static validation of a satellite honeycomb sandwich structure
Engineering Solid Mechanics
The honeycomb sandwich structures are extensively utilized in the satellite load bearing structure due to their superior mechanical properties. Investigating such structures and establishing their failure map implies the estimation of their equivalent elastic parameters as well as the experimental measurements of their ultimate strengths. Through a comprehensive study, this article discusses thoroughly the mechanical behavior of an aluminum honeycomb structure exposed to flat-wise compressive and flexural testing. Furthermore, an equivalent finite element model, based upon the sandwich theory, is proposed for simulating the elastic behavior of the flexural testing and comparing computational and experimental results. The comparison of results confirms accurately the usage of the sandwich theory and its related shell-volume-shell approach in the efficient modeling of honeycomb sandwich structures. In addition, the aforementioned honeycomb structure is parameterized from the geometry and material perspective. The outcome of such study reveals that the honeycomb core thickness has the greatest influence on the maximum displacement value. In addition, aluminum alloys are optimum choice for facing sheets material of the honeycomb structure.
Experimental and Numerical Analysis of Critical Buckling Load of Honeycomb Sandwich Panels
Journal of Composite Materials, 2010
The critical buckling loads for various core densities and materials of honeycomb composite panels are experimentally and numerically investigated in this study. The surface plates of honeycomb composite panels are of polyester/glass fiber composite. Polyester resin-impregnated paper or aluminum is used as the honeycomb core material. Honeycomb panels with different cell sizes, but approximately the same volume, are produced and the effect of the honeycomb core density on the critical buckling load is investigated by compression tests. The critical buckling load of paper core panels is determined to be higher than that of aluminum core panels. It is seen that the buckling strength of the specimens increases by the increase of core density. As the critical buckling load exceeds a certain limit, regional core cell buckling and core crushing are seen in aluminum core panels. In paper core panels, regional cracks are seen, in addition to these failures. The study also calculates the num...
Three Point Bending Analysis of Honeycomb Sandwich Panels: Experimental Approach
Recent trends in modern railway industry shows more and more use of composites specially sandwich structures to build the coaches so as to achieve higher speeds, reduced power consumption and increase in pay load carrying capacity. Honeycomb sandwich structures have wide applications as structural and non-structural materials of the coaches in the railway industry. A sandwich construction consists of two thin facing layers separated by a thick core. Static three-point bending tests were carried out in order to investigate the failure loads. ASTM C 393 standards are followed for the experimental approach.