Composite sandwich structures are becoming more and more popular in the sports, automotive, and aerospace sectors because of their excellent strength-to-weight ratio. However, more research is required to fully understand their stiffness properties and the accuracy of predictive modeling. By simulating and examining two different sandwich structures made of Carbon fiber face sheets and Kevlar honeycomb core material represented as an equivalent solid, this study fills this gap. The Gibson and Ashby model has been adopted to find the equivalent orthotropic properties of the core because this model provides a balance between precision, computational efficiency, and suitability for honeycomb cores, guaranteeing accurate stiffness predictions and facilitating simple engineering design implementation. Experimental stiffness values of 529.74 N/mm and 479.98 N/mm for the two configurations are obtained by performing a “Three Point Bend Test” on the manufactured panels. With an accuracy deviation of about 0.84%, the numerical model predictions closely resemble the experimental findings, demonstrating the model’s dependability in representing the material’s static behavior. The sandwich structure demonstrates a stiffness of about 565 N/mm, suitable for high-load applications in aerospace and automotive sectors. Numerical modeling effectively validates the experimental results by accurately predicting the stiffness of Kevlar honeycomb core sandwich panels.

In the aerospace industry, the usage of sandwich panels in a variety of space structures such as satellites is increasing due to their excellent features like high strength-to-weight ratio, and thermal insulation. These structures are subjected to a variety of thermal loads depending on their working conditions, which cause them to expand or contract. Since these panels are connected simultaneously by twists, buckling is possible due to thermal loads. In this paper, the thermal buckling analysis of a CCCC Aluminum honeycomb core sandwich panel is performed under asymmetric thermal loading, using ABAQUS. The face sheets are attached to the core by adhesive. Thermal loading is assumed to be two heat fluxes of 70 watts and 20 watts, which are asymmetric, and face sheets radiate heat to their surroundings. The modeling results showed the panel does not buckle under the mentioned thermal loading. The critical buckling stress is 750 MPa and 400 MPa where the maximum thermal stress is 95 MPa and 37 MPa for vertical and horizontal edges respectively, which shows a significant difference of 8 to 11 times. The temperature distribution of the various points of the panel was also obtained by calculating the maximum temperature of 84 °C at the 70-watt heat flux location and the minimum temperature of 15.65 °C in the lower-left corner. The influence of various parameters like face sheets and core cell wall thickness on buckling occurrence is also discussed.

Failure maps of sandwich panels such as beam, plate and shell are of great importance in designing such structures. In this paper, failure maps of sandwich beams with composite skin and honeycomb core are obtained. The effect of transverse shear in skins and core and the effect of double walls of honeycomb core have been taken into account. Shear deformation of skins and core are assumed to be linear. By minimizing the potential energy equation, the shear deformation coefficients of core and skins are obtained. Axial stresses in skins and core are obtained in terms of these coefficients. core is assumed to have orthotropic properties.Three point bending tests have been performed on some sandwich beam specimens. It is found that specimens for which failure load and its corresponding failure mode lie away from the boundary lines in failure map, there is a little difference between failure loads obtained from theories and experiments but this difference is more significant near the boundary lines due to combination of failure modes. In the case of transverse ribbon direction, the theoretical and experimental results are closer.

In this paper, an analytical solution for the static indentation and low velocity impact response of composite sandwich beams with an orthotropic symmetric composite face-sheets and foam or honeycomb core is presented. The indentation force during impact loading consists of two regimes, one for small indentations of the top face-sheet due to bending moments and the other for larger deformation due to membrane forces. Also, the crushable core is considered a rigid-plastic foundation, and the elastic aspect is neglected. To obtain a more accurate approximation of the static indentation of the beam, both the local and global deformation of the sandwich beam are considered. The minimum potential energy method is applied for the extraction of governing equations. Furthermore, by developing a three dimensional finite element model through the ABAQUS code, the low velocity impact on composite sandwich beams with foam core is simulated. The contact force history, maximum contact force, and upper face-sheet displacement results computed by the analytical model are compared with experimental and ABAQUS simulations. A good agreement between the analytical model, finite element simulation, and experimental results, is observed.

The main goal of this paper is to introduce an isogeometric analysis (IGA) procedure based on Reddy’s higher-order shear deformation theory (HSDT) for vibration analysis of sandwich plates resting on Kerr foundation (KF). The sandwich plates include the ultra-light feature of the auxetic honeycomb core layer and are reinforced by two laminated three-phase skin layers. The governing equation is derived from Hamilton's principle. The Newmark-beta method is applied to solve the vibration characteristics of the sandwich plates using the code in Matlab software. The reliability and accuracy of the proposed formula are verified through comparative examples. Additionally, the effects of geometrical dimensions, material properties, boundary conditions (BCs), and foundation stiffness on the vibration of sandwich plates are studied in detail. Our findings indicate that the initial geometry of the auxetic honeycomb core has a significant impact on the vibration characteristics of sandwich plates.