جستجوی مقالات مرتبط با کلیدواژه « لانه زنبوری » در نشریات گروه « مکانیک »

In this article, to investigate the severity of damage to the helicopter pilot under the crash impact, the numerical simulation of the actual helicopter cockpit seat has been done. To limit the complexity of the problem, a fully vertical impact was considered as a reference scenario for the assembly consisting of a collapsible helicopter seat, an energy absorption section, and a humanoid dummy. For this purpose, the three-dimensional model of the chair in the laboratory was studied in two states with and without the addition of the energy absorption mechanism. A honeycomb structure was used in the seat cushion section. The results of the research showed that the use of UPVC damper to test the crash impact with a certain mass based on biomechanical criteria, an average 80 % decrease in serious injuries to the skull and spine has been achieved. Also, based on the results obtained in this research, although the aluminum honeycomb structure meets the criterion of damage to the head and is within the permissible range, it has rejected the criteria of damage to the spine and permissible acceleration range. However, compared to the case without honeycomb, it has performed much better and has been able to absorb the energy of the crash impact.

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.

In axial flow compressor there is a gap between stationary and rotating members since the stator vane is fixed at the casing and the shaft is rotating at the root. Also, the pressure increases when the air flows through the stator vanes. Therefore, due to pressure increase and existence gap under vanes, the leakage is inevitable in the stator tip. This leakage can change the flow pattern near the stator tip, which causes more separation. Therefore the loss has been increased so it adversely effects on performance. In this paper, the effect of stator tip sealing with honeycomb on compressor performance is investigated. For this purpose, the 9th stage of a ten-stage compressor is examined in two cases of solid wall and sealing with honeycomb. The numerical results have good agreements with experimental results. The results show that by reduction of leakage at stator tip, the size and depth of tip corner separation decreased significantly leading to loss reduction. Also the effect of the leakage on flow angles shows that to have more accurate analysis of compressor performance, it is necessary to be considered the stator tip leakage. On the other hand, according to same effect of honeycomb on reducing stator tip leakage than solid wall, here the honeycomb roles as an abradable material to prevent direct contact between rotor and stator. Also in analysis of stage the honeycomb can be replaced with solid wall model.

In this paper deflection and free vibration of sandwich panel is studied. The core of Sandwich panels is made of hexagonal honeycomb and faces are made of two different materials of Carbon Fiber Reinforced Plastic and K-aryl/epoxy covering. The governing equations are deduced from the First order Sheer Deformation Theory (FSDT) and they are solved using Generalized Differential Quadrature Method (GDQM). The classical method in the references is used to verify the DQ method and to show that the applied GDQM method has a good results with compared to the references. Deflection of sandwich panel is investigated with two different load types. Finally natural frequency for the first 4 modes and the two different faces materials are calculated and the effect of various lengths to core thickness ratios and faces to honeycomb core thickness ratios are studied. Further, the effect of foundation stiffness coefficient on deflection and natural frequency are showed.

In this paper deflection and free vibration of sandwich panel is studied. The core of Sandwich panels is made of hexagonal honeycomb and faces are made of two different materials of Carbon Fiber Reinforced Plastic and K-aryl/epoxy covering. The governing equations are deduced from the First order Sheer Deformation Theory (FSDT) and they are solved using Generalized Differential Quadrature Method (GDQM). The classical method in the references is used to verify the DQ method and to show that the applied GDQM method has a good results with compared to the references. Deflection of sandwich panel is investigated with two different load types. Finally natural frequency for the first 4 modes and the two different faces materials are calculated and the effect of various lengths to core thickness ratios and faces to honeycomb core thickness ratios are studied. Further, the effect of foundation stiffness coefficient on deflection and natural frequency are showed.

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.

In this study, honeycomb energy absorber is optimized using genetic algorithm. The design goal is to absorb whole impact energy within a ‎limited shock load level. First the crashworthiness and parameter sensitivity of honeycomb structure is extracted as explicit functions that ‎are utilized to find optimized shock absorber configuration. Energy absorber must depreciate the impact kinetic energy and mitigate its ‎defects on the structure and aboard. So the energy absorption capacity while the shock load is kept limited are the main design objectives. ‎The volume and mass restrictions are also important objectives from an application point of view. Based on the simulation results ‎available in the article Part I, the honeycomb response surfaces of crashworthiness parameters including the mean and peak crushing ‎stresses are extracted. Utilizing the genetic algorithm based on response functions, the multi-objective optimized energy absorber is ‎investigated. The main objective of the optimization problem is set to minimization of mass or volume while the maximum allowable shock ‎and minimum energy absorption capacity are included as the problem constraints. The geometric specifications of honeycomb structure ‎including cell-size, foil thickness, height and absorber face area are among the design variables with optimization outputs of energy ‎absorption capacity, volume, mass, and shock level. Some optimization results are compared with those available in the literature and a ‎typical problem is handled. Results show that mass and volume optimized geometries are almost similar and reduction of acceptable shock ‎level makes the optimized geometry height to rise.‎

In this study, the design and optimization of a honeycomb energy absorber is performed using genetic algorithm. The main design goal is to absorb almost whole impact energy. Simultaneously, the reducing of the shock force level is also considered as a main objective. In the first part, the crashworthiness behavior of honeycomb structure is parametrically studied. The results are utilized in the second part to optimize shock absorber design. In this part, aluminum honeycomb structure under dynamic loading is investigated using simulation in LS-dyna finite element code. Parametric studies are invoked to identify the influence of different model parameters on crashworthiness characteristics of honeycomb structure. Reducing the computational cost, a repeatable model of 'Y' cross section column is numerically simulated. The effects of changes in material properties including Young's modulus, yield stress, tangent modulus, geometrical properties such as cell size, foil thickness, as well as the effects of impact velocity on the deformation behavior of the structure were investigated. A number of 25 different geometries with same height and various cell sizes and thicknesses are studied and effects of thickness and cell size on the energy absorption properties is investigated. Results showed that crashworthiness parameters such as mean and peak stress depend mainly on cell size and thickness values, while the friction coefficient and young's modulus are of less importance. Any change in absorber’s geometry affects the mean collapse stress more severe than the peak stress. In the meantime, thickness change is more effective in comparison with cell size change.

Wind tunnels generate controlled air flow which passes through the model. Thus، a series of useful data related to air flow quality are obtained. The final goal of wind tunnel design is to generate a uniform air flow with minimum turbulence intensity and low flow angle. One of the methods for decreasing the turbulence intensity is to install honeycomb and screens in the settling chamber of the wind tunnel. In this research، the effects of honeycomb and screens with specified geometric parameters on velocity distribution، turbulence intensity، skewness and flatness are investigated. A set of hot-wire anemometer is used to measure turbulence intensities. It measures flow instantaneous velocity with high frequency. The results show that the installation of honeycomb and screens، and isolation of the test section from the fan decreases the turbulence intensity of the test section about 75% and، optimizes the skewness and flatness values. Moreover، normal probability distribution of instantaneous velocity approaches the normal distribution.

In this research, influence of foam filling technique in honeycomb cores by using lightweight rigid polyurethane foam is investigated. Plastic mechanical behaviors of honeycomb cores are studied by mean of numerical method. Four types of Aluminum honeycombs (Al 5052 alloy) both bare and foam-filled were subjected to unidirectional compression. Analyses were carried out for different impact velocities to survey quasi-static and dynamic crushing response of the honeycomb cores. Crushing strengths and specific absorbed energy were obtained for honeycomb cores which have different relative densities. FEM results showed that foam filling technique can increase crushing strength of honeycomb core up to 24 times, and its specific absorbed energy up to 11 times. However, it was found that in heavier honeycombs the effect of foam filling technique decreases significantly. Furthermore, it was found that in quasi-static situation, foam filling technique can enhance desired core mechanical properties’. Meanwhile, in dynamic states of impact it was illustrated that polyurethane foam have not significant role in improving crushing strength and specific absorbed energy of honeycomb cores. For instance, in crushing with impact velocity of 100 m/s, amount of specific absorbed energy for bare and foam-filled cores were approximately equal.

In this paper, ballistic impact on sandwich panel with composite face sheet made of Glass/Epoxy and aluminum honeycomb core has been studied. The solution is derived from a wave propagation model. At first both analytical and numerical solutions were clarified and their results were compared with experimental results. Some deformation patterns, failure modes and energy absorption mechanisms were identified by observation, such as: dynamic movement of the target, stretching, bending deformation, delamination, debonding, shear fracture honeycomb, tensile fracture of Glass/Epoxy and plug and petal formation in composite facings. The solution involves a four-stage and effective masses of the face sheets and core as the shock waves travel through sandwich panel are derived using Lagrangian mechanics. The resulting non-linear differential equation of motion was solved considering the local damage effects and corresponding energy absorptions. Also numerical model, analysis of the penetration process was performed by a nonlinear explicit finite element code, LSDYNA. The results of analytical solution and numerical simulation are compared with experimental tests. 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.

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.

Honeycomb is one of the major components of a wind tunnel, which is used to make the air flow uniform and reduce the flow angle. A honeycomb is installed upstream of the nozzle in the settling chamber. As high costs are incurred for construction of honeycomb in large vertical wind tunnels, and in view of the difficulties in installation of these units, it is necessary to reduce the ratio of length to hydraulic diameter of the honeycomb. However, reduction of this ratio may affect the honeycomb performance. In this paper, various honeycomb designs have presented and flow quality has been experimentally investigated for each case. A hot wire anemometer (HWA) and a device for measurement of flow angle (yaw head) have been used to study the flow downstream of the honeycomb. Results show that with decrease in length to hydraulic diameter ratio from 7 to 2, the honeycomb performance is adequate for change in flow angle from -20 to 20º. These results have been used in the design of a vertical wind tunnel, namely Tofan Vertical Wind Tunnel, which will be used for the simulation of skydiving. Based on these results a square honeycomb of length to hydraulic diameter ratio of 2 has been selected, which has resulted in a reduction of up to 60% in the construction cost of the honeycomb.