Papers by Keyword: Honeycomb Sandwich Panel

Abstract: An aluminous honeycomb sandwich panel with some structural damages was selected as the objective in this study. The panel was simply supported along four edges and its natural frequency data was collected through modal experiment with a hammering method. Application of frequency dactylogram method for honeycomb sandwich panel damage is identified. The detection results show that the frequency dactylogram method can be constructed using the frequency data of honeycomb sandwich panel, which is only related with the positions of damage and not the degree of damage.

Abstract: In this study, the elastic-viscoplastic properties of aluminum honeycomb sandwich panels are investigated using a homogenization theory for free edge analysis. For this, the mathematical homogenization theory is reconstructed for elastic-viscoplastic analysis of honeycomb sandwich panels by introducing a traction free boundary condition. Moreover, the domain of analysis is reduced to a quarter using point-symmetry of internal structures of honeycomb sandwich panels. The present method is then applied to the analysis of macroscopic elastic-viscoplastic behavior and microscopic stress distribution of an aluminum honeycomb sandwich panel subjected to in-plane uniaxial compression. It is shown that the stress concentration arises at face/core interfaces, especially at intersections of core walls.

Abstract: In this study, the relationship between the impact performances of light-weight honeycomb sandwich composite panels with design parameters like panel cores and face’s thicknesses and materials, honeycomb foil thickness and cell size etc. are experimentally evaluated through the spindle falling tests. Analytical approaches are also carried out to confirm the validity of the experiments based on 3D modeling and using ANSYS LS-DYNA software. Comparisons of the experimental and analytical results are reported in this study.

Abstract: This paper first studied aluminum alloy honeycomb sandwich panel in out- plane static compress test.Through analyzing deformation characteristics, the loads-displacement relationship was obtained and are described by the average stress-strain curve. Secondly, using the Split Hopkinson Pressure Bar device of impact test, deformation behaviour，dynamic average stress-strain curve data and so on were got under different loading rates, thus learned impact dynamics characteristics of that.

Abstract: Finite element analysis of honeycomb sandwich panel has been performed by modeling the structure through three different approaches. Continuum properties are calculated through analytical solution and verified through FE analysis of bare core. In addition to that the thickness of core has also been varied in all the three approaches in order to study its effect on vibration analysis of sandwich structure.

Abstract: A computational model, which can reveal the out-plane size variation of sandwich panel unit cell, is proposed to study the out-plane size effects of honeycomb sandwich panels. In this model, the three dimensional unit cell of sandwich panel, consisting of the upper and the lower skins and the homogenized core, is constructed based on homogenization method. Three methods, i.e., homogenization method, the finite element method and the classical laminated plate theory, are used to study the influences of the out-plane size variation on the bending effect and vibration response of sandwich panel. Numerical results show that the solution of finite element method agrees with that of laminated plate theory when the number of out-plane unit cell is small. However, once the number of out-of-plane unit cell is large enough, the finite element solution is close to the homogenization results.

Abstract: This paper describes the results of an experimental investigation on the drop off impact test on a range of sandwich panels. The magnesium alloy sandwich panels were fabricated with rolled sheets at different thickness by pressing and bonding method. Out-plane compression test was employed to obtain its basic deformation-force behavior. The impact experiments were carried out in which a steel cylinder was dropped off at various height levels, ranging from 0.5m to 1.5 cm to impact the panel. A high speed camera was employed to take pictures at 20 thousand frames per second and the low-velocity impact response on the sandwich panels is recorded with a dynamic force senor under the panel simultaneously. The shock response with time and the impact absorption energy were analyzed and compared. The results of this study proved that the magnesium alloy honeycomb sandwich panels have good impact energy absorption performance.

Abstract: According to the structural layout and mechanics characteristic of microsatellite, the FEM was established reasonably. Base on the FEM analysis and its characteristics, the structure of microsatellite was optimization designed. In the optimization process, the optimization model was established with the design variables of aluminum panel thickness, core plate thickness and skeleton thickness, and subjected to stiffness, strength, displacement and size constraints. Then, used the sequential quadratic programming method for optimization analysis. The results of the optimization demonstrates that the weight of structure loss significantly, and the whole structure weight of the microsatellite loss 11%.Meanwhile, the iterative times of the optimization process is few, so it is very Meaningful and useful for actual project application.

Abstract: With the honeycomb sandwich structure widely used in aerospace, the research of its mechanical properties becomes especially important. All of the finite element analysis software have no corresponding cell library, so before the analysis, the honeycomb sandwich panels should be equivalent processed. The paper by taking the floor of a microsatellite as the research object, used the equivalent plate theory and sandwich plate theory for equivalent processing, then adopted the finite element software to analyze the mechanical properties of the floor under two alternative condition. By compared with analytical solution, the equivalent results were reasonable, and the two methods were basically identical. Meanwhile, the equivalent results provided the reliable basis for the satellite structure optimum design and mechanical test.