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A honeycomb panel consists of an array of open hexagonal cells which their walls are perpendicular to face sheets although other panel sandwiches don’t have these perpendicular walls. Their design is often performed based on minimum weight. This research is aimed at minimizations of weight by means of computing honeycomb core girth. Weight optimization is done by means of Naive and numerical procedures. Numerical optimization is done by the sequential quadratic programming (SQP) method. Geometric parameters and optimized weight are calculated for hexagonal and square cells. Optimized weights for these two cross-sections are compared. Keywords: Honeycomb Weight Optimization, Sandwich Panels, Numerical optimization, Sequential Quadratic Programming.

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Sandwich panels have high strength to weight ratio because of their special structure. The variables which are defined for designing sandwich panels should be determined with applying necessary strength and lowest weight. In this paper, the imperialist competitive algorithm (ICA) has been used for minimizing the weight of a sandwich panel with prismatic core based on yielding and buckling criteria. ICA is inspired of imperialist competitions and it is based on two special criteria as recruitment policy and stable imperialist competition. Arrays numbers, core and surface thickness and panel height are assumed as design variables for decreasing panel weight. The results were shown that core and surface thickness and the total height of panel has been increased by increasing loading for given number of arrays. Also the core and surface thickness has been decreased and the total height have been increased by increasing array number for a determined loading and so panel weight has been decreased. A panel with diamond core has highest structure efficiency. It was shown that ICA is useful and competitive than the other heuristic algorithms because of direct using of function values in some problems which was required to the total optimization.

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In this paper, a new analytical model has been presented for energy absorption of aluminum-foam sandwich panels under ballistic impact. The panels consist of foam core sandwiched between two aluminum skins. In analytical model two types of sticker including cylindrical projectile with flat and hemispherical ended have been considered. It is supposed that aluminum skins failure by mean resistive pressure. Also foam absorbed a partial of projectile energy by crushing. Energy absorption of aluminum-foam sandwich panel is calculated and energy balancing equation has been employed for determination the ballistic limit and residual velocity of projectiles. The results of ballistic limit and residual velocity computed by new model have good agreement with experimental results. Also the effects of projectile mass and diameter in energy absorption of sandwich panel has been investigated.

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In this paper, multi-objective optimization of sandwich panels with open and prismatic core has been studied. Naming these panels is based on the number of corrugations (n) of the core. The panel is considered as a heat exchanger that is loaded under longitudinal loading simultaneously. Multi-objective particle swarm optimization (MOPSO) is used by considering weight and heat transfer index as objective function. Optimization is carried out so that the panel has minimum weight and maximum heat transfer index simultaneously, moreover it will not suffer from yielding and buckling in face and core plates. The results showed that two panels, i.e. n=1 and n=7 are very suitable in one-objective and two-objective optimizations. Also, maximum of heat transfer index obtained by a certain panel is nearly the same in various loadings. Pareto diagrams achieved out of two-objective optimization have two separate areas where in one area weight increase may cause an intense increase in heat transfer index and in another area this index remains almost constant. The diagrams are helpful in selecting suitable panel and its geometric dimensions based on significance of each objective functions. Comparing the results indicate efficiency of PSO method in one-objective and two-objective optimization of the panels.

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this paper, ballistic impact on sandwich panel with composite facesheet made of Glass/Epoxy and aluminum honeycomb core has been investigated experimentally. Ballistic impact test also carried out on Honeycomb and composite and the effect absorption energy by adding composite on two sides honeycomb is studied. By this model the influence of the components on the behavior of the sandwich panel under impact load was evaluated. Ballistic impact tests is carried out on the samples by flat-ended projectile with 8/5 gr mass and 10 mm diameter in difference velocities. Also, the contribution of the failure mechanisms to the energy absorption of the projectile kinetic energy was determined. The results show that honeycomb sandwich has more energy than when alone ballistic tests conducted on has absorbed and front cover compared with back cover sandwich structure has lower energy absorption. Also bigger than ballistic limit velocity absorbed the maximum amount of energy.

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In this study, single-objective and multi-objective optimization of curved sandwich panel with composite face sheets and magneto-rheological core have been done to maximize the first modal loss factor and minimize the mass by using genetic algorithm. The studied sandwich panel was curved with simply support boundary condition. In order to derive the governing equations of motion, an improved high order sandwich panel theory and Hamilton's principle were used for the first time. The face sheet thickness, core thickness, fiber angles and intensity of the magnetic field have been considered as optimization variables. In single-objective optimization, the optimized values of variables were calculated. The results showed that the structures tend to have thick core and thin face sheets which seems physically true. As the magneto-rheological fluid placed in the core, it has a significant effect on the increasing of the modal loss factor. For the multi-objective optimization the Pareto front of optimal technique was presented. Then for the first time at this field, the set of optimal points are selected based on TOPSIS method and it was showed that in the case of similar size and mass, modal loss factor of double-curved panel is more than sigle-curved.

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A novel geometrically nonlinear high order sandwich panel theory considering finite strains of sandwich components is presented in this paper. The equations are derived based on high order sandwich panel theory in which the Green strain and the second Piola-Kirchhoff stress tensor are used. The model uses Timoshenko beam theory assumptions for behavior of the composite face sheets. The core is modeled as a two dimensional linear elastic continuum that possessing shear and vertical normal and also in-plane rigidities. Nonlinear equations for a simply supported sandwich beam are derived using Ritz method in conjunction with minimum potential energy principle. After obtaining nonlinear results based on this enhanced model, simplification was applied to derive the linear model in which kinematic relations for face sheets and core reduced based on small displacement theory assumptions. A parametric study is done to illustrate the effect of geometrical parameters on difference between results of linear and nonlinear models. Also, to verify the analytical predictions some three point bending tests were carried out on sandwich beams with glass/epoxy face sheets and Nomex cores. In all cases good agreement is achieved between the nonlinear analytical predictions and experimental results.

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Sandwich panels due to high strength to weight ratio and energy absorption properties, are widely used in various industries including aerospace industries, marine and automotive industries. Analysis of ballistic resistance of sandwich panels is mainly numerical and experimental, and there are a few analytical models in this field due to mathematical complexities. Hoo Fatt et al. have studied analytically high velocity impact on sandwich panels with composite skins and foam core. Because of the widespread use of sandwich panels with metal face-sheets and foam core in aerospace industry, by modifying the analytical method provided by Hoo Fatt et al. the ballistic resistance of the foam core sandwich panels with metal surfaces impacted by high velocity cylindrical projectile is analytically investigated in this paper. Two types of panels with polymeric and metallic foam cores and aluminum surfaces have been used to assess the accuracy of the analytical method. Results show that the proposed analytical method can predict the residual velocity of the projectiles impacted at high velocities on the foam and metallic core panels with different relative densities of the core.

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Sandwich structures have low weight and high stiffness. Sandwich panels with open and prismatic cores are a kind of these structures that have special properties. These panels are named based on the number of corrugations (n) of the core. In this paper weight optimization of these panels is carried out by Gravitational Search Algorithm based on yielding and buckling constraints. This algorithm is a heuristic algorithm that is based upon the Newtonian gravity force and the laws of motion. For optimization of the weight, core and surface thickness and panel height are assumed as design variables. The results show that for a specific panel, the design variables and the weight of panel are increased by increasing the load. Also the core and surface thickness are decreased and the weight and panel height are increased by increasing core corrugate number at a specific loading. The panels with n=1 and n=2 have the minimum weight and highest structural efficiency. By comparing the results with some previous studies, it is shown that the Gravitational Search Algorithm is a useful tool in achieving lower weight in these panels and has a good convergence rate.

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A novel geometrically nonlinear high order sandwich panel theory for a sandwich beam under low velocity impact is presented in this paper. The equations are derived based on high order sandwich panel theory in which the Von-Karman strains are used. The model uses Timoshenko beam theory assumptions for behavior of the face sheets. The core is modeled as a two dimensional linear elastic continuum that possessing shear and vertical normal and also in-plane rigidities. Nonlinear equations for a simply supported sandwich beam are derived using Ritz method in conjunction with minimum potential energy principle. After obtaining nonlinear results based on this enhanced model, simplification was applied to derive the linear model in which kinematic relations for face sheets and core reduced based on small displacement theory assumptions. A parametric study is done to illustrate the effect of geometrical parameters on difference between results of linear and nonlinear models. Also, to verify the analytical predictions some low velocity impact tests were carried out on sandwich beams with Aluminum face sheets and Nomex cores. In all cases good agreement is achieved between the nonlinear analytical predictions and experimental results.

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This study dealt with the flutter and biaxial buckling of composite sandwich panels based on a higher order theory. The formulation was based on an enhanced higher order sandwich panel theory that the vertical displacement component of the face sheets were assumed as quadratic one while a cubic pattern was used for the in-plane displacement components of the face sheets and the all displacement components of the core. The transverse normal stress in the face sheets and the in-plane stresses in the core were considered. For the first time, the continuity conditions of the displacements, transverse shear and normal stress at the layer interfaces, as well as the conditions of zero transverse shear stresses on the upper and lower surfaces of the sandwich panel are simultaneously satisfied. The aerodynamic loading was obtained by the first-order piston theory. The equations of motion and boundary conditions were derived via the Hamilton principle. Moreover, effects of some important parameters like lay-up of the face sheets, length to width ratio, length to panel thickness ratio, thickness ratio of the face sheets to panel, fiber angle, elastic modulus ratio and thickness ratio of the face sheets on the stability boundaries were investigated. The results were validated by those published in the literature. The results revealed that by increasing length to width ratio, length to panel thickness ratio and elastic modulus ratio of the face sheets, the stability boundaries were decreased and the largest nondimensional buckling load was occurred at the angle ply sandwich panel.

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In this paper, the interaction between aluminum facing and honeycomb structure in the quasi-static and the impact loading has been investigated experimentally. The structural elements used in this research were aluminum plate, aluminum 5052 honeycomb structure. The quasi-static penetration tests and ballistic impact experiments were performed on aluminum plate, honeycomb structure and sandwich panel by flat ended penetrator and flat ended projectile respectively. The failure mechanisms, the ballistic limit velocities, the absorbed energies due to penetration, the damage modes and some structural responses were studied. Also, the effect of interaction between aluminum facing and honeycomb structure in the quasi-static penetration and the ballistic impact response in this honeycomb sandwich panel was discussed and commented upon. Comparing energy absorption in these structures showed that the amount of absorbed energy by the sandwich panel with honeycomb core is more than the absorbed energy by the aluminum plate and honeycomb structure in the quasi-static penetration. These results indicated, when the honeycomb structure was used as the core of sandwich panel, resulted in increasing of the stiffness and the strength of the sandwich panel. The ballistic impact results showed that the absorbed energy and the ballistic limit velocity in the sandwich panel compared with the individual components was increased. Therefor the sandwich structure can be used as a suitable energy absorber.

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In this research the possibility of mass reduction in a two-module cubic microsatellite with skin – frame structure is studied. Natural frequencies and effective mass distribution change by replacing isogrid structure with sandwich panel (honeycomb). Modal effective mass is a dynamic characteristic of structure and depends on natural frequencies, mode shapes, general masses and eigenvectors. Modal effective mass is a quantity that shows the importance of a mode when satellite is under acceleration loads through the baseplate. High modal effective mass shows high reaction loads on baseplate in corresponding frequency. Also acting dynamic loads are affected by distribution of modes in frequency range. The sum of effects of different modes creates significant reaction loads. Hence, study of frequency and effective mass changes by converting the structure design from isogrid to sandwich structure is necessary. In this paper, first two isogrid and sandwich structures with equal masses are compared. Then mass of sandwich structure is decreased such a way that natural frequencies of light sandwich structure approach natural frequencies of isogrid structure. In equal masses case, natural frequencies of sandwich structure are twice the natural frequencies of isogrid structure but effective mass distribution of isogrid structure is better along the launch direction. By changing the isogrid structure design to sandwich panel structure and optimization of the new structure characteristics a noticeable reduction in mass and improvement in modal behavior could be obtained.

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Hybrid laser-arc welding is a new welding process which received particular attention in various industries because of its technological and economic advantages. This process combines a laser beam and an electric arc to incorporate the advantages of both laser and arc welding processes. The main goal of this paper is to evaluate the performance and ability of hybrid Nd:YAG laser-TIG welding compared to lone laser welding process for welding of aluminum foam sandwich (AFS) panels of AA6082. For this aim, a set of experiments for both laser and hybrid laser-TIG welding were done to investigate the effects of welding parameters including laser power, arc current and welding speed on weld dimensions. Then, appropriate welding parameters for the laser and hybrid laser-TIG welding of AFS panels were calculated by statistical analysis. The results show that laser power threshold for creating the keyhole was less in hybrid laser-TIG welding than lone laser welding. Moreover, increasing the laser power and decreasing the welding speed result in increasing both the weld depth and width. But, with increasing the arc current, the weld depth remains almost unchanged and only the weld width increases. Comparing the laser and hybrid laser-TIG results show that adding a 100 A arc to a 2000 W laser source can increase the welding speed from 2 to 3 m/min which prove the high ability and efficiency of hybrid laser-TIG welding process.

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In this paper, the behavior of free vibrations and buckling of the thick cylindrical sandwich panel with a flexible core and simply supported boundary conditions using a new improved ‎high-order sandwich panel theory were investigated. An axial compressive load is applied on the edges of the top and bottom face sheets simultaneously. The formulation used the third-order polynomial description for the displacement fields of thick composite face sheets and for the displacement fields in the core layer based on the displacement field of Frostig's second model. In this model, there are twenty seven degree of freedom. The transverse normal stress in the face sheets and the in-plane stresses in the core were considered .For calculated exact solution, according to thick face sheets, all of the stress components were engaged. The equations of motion and boundary conditions were derived via the Hamilton principle. Moreover, the effect of some important parameters such as those of thickness ratio of the core to panel, the length to radius ratio of the core, cumferential wave number and composite lay-up sequences on free vibration response and buckling of the panel were investigated. In order to validate the results, the obtained results were compared with those obtained using finite element ABAQUS software. The advantage of this paper is simplicity, considering face sheets as thick, exact solution and the considering of important terms such as (1+z_c/R_c ) in equations.

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Large and/or complicated sandwich structures are often manufactured by connecting pre-fabricated sandwich panels by means of connections, adhesive or bolts. In nearly all sandwich constructions certain types of joints have to be used for assembly but little is known about their mechanical behavior. This paper deals with the investigation of the behavior of two aluminum joints with different geometries under low velocity impact tests. These two joints are used to connecting sandwich panels with glass-epoxy skins and aluminum honeycomb core. The joints and sandwich panels are connected by means of epoxy resin. After construction of the specimens, low velocity impact tests were performed on the specimens. Finite element analysis were used to simulate the behavior of sandwich panels with connection. Verification of the numerical results was performed by comparing the numerical and experimental results. There was a good compliance between numerical and experimental results. Also, the effect of increasing the length and the thickness of the connections on the behavior of the sandwich panel was done through a parametric study using the FEM model.

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Metal faced Polyurethane/Polyisocyanurate sandwich panels are used in construction sites and temporary accommodation especially after destructive events such as flooding and earthquake, that a clear example was the temporary settlement of earthquake victims after earthquake occurrence in the Kermanshah province at November 2017. However, flammability of polyurethane foam core of these panels and the higher risk of fire in these types of buildings, highlight the importance of assessing fire performance of these panels.In this study, fire performance of several types of metal faced sandwich panels with PUR/PIR foam core produced in the country, was evaluated by reaction to fire and fire resistance tests. The reaction to fire behavior of foams was also evaluated separately. The results showed that the polyurethane foam was not fire retarded and met reaction to fire class F; but the poly-isocyanurate foam depicted a better fire behavior and met fire class E. Fire resistance tests were performed on common types of sandwich panels in the temporary buildings with two different execution details including a steel sheet fixed to the joint position in the panels and the other, fireproof paint and their fire performance was compared to unprotected panel. According to the results, deformation of the joint in sandwich panel is the main disadvantage and it is very critical in real fire due to flame spread through the joints which is critical in a real fire incident, when evacuating the occupants and acting fire brigades. Hence, protection of the joints by insertion of a protective sheet, increases fire resistance and improves the integrity by increasing the time by 40 minutes compared to the unprotected panel. Finally, fire safety recommendations were provided for the safe use of these panels in temporary buildings.
 

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The sandwich panel is a combination of a soft core and two stiff, high-strength facesheets. In many cases, the connection between the facesheet and the core is considered as a critical point that can damages the integrity of the sandwich structure. In this study, the debonding toughness between the facesheet and the core in sandwich beams with grooved cores made of Kevlar 49/polyester facesheets and polyurethane foam core has been measured experimentally. The values ​​of the strain energy release rate obtained at the onset of crack growth for the tested specimens are in the range of 340 (J/Square meters) and increase with the crack growth up to 500 (J/Square meters). One of the innovations of the present study is to investigate the effect of grooving the core of the sandwich panel on the resistance of the structure to the growth of interfacial cracks. The results show that by placing the groove inside the core of the sandwich panel, the interfacial crack stops during growth by hitting each groove and requires higher force to restart its growth. This phenomenon increases the resistance of this type of structure against the growth of cracks in the face/core area. In this research, a model based on cohesive zone theory was used to simulate crack growth in the tested specimens. Comparison of load-displacement curves obtained from the analysis shows that the proposed model has a good ability to predict the behavior of the structure under similar loading conditions.