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This paper presents the problem of nonlinear aero-thermo-elastic response of cracked plate. Bending equations of two-dimensional simply supported cracked plate subjected to supersonic flow and thermal effect is derived based on classical plate theory (CPT) and Von Kármán nonlinear relations. Linear piston theory is utilized to evaluate the aerodynamic pressure with uniform temperature variations. By applying Galerkin's method and Runge-Kutta scheme, the equations are solved. The effects of parameters such as flow condition, crack dimension, temperature changes, plate aspect ratio, mass ratio, static pressure on the plate stability, flutter point and limit cycle oscillation (LCO) of the plate are examined. [ABSTRACT FROM AUTHOR]

Shape memory effect is the key factor in the design of self-reconfigurable core using origami. Effects of heat treatment on transformation temperatures and stress-strain curve of shape memory alloys using differential scanning calorimetry and tensile testing is presented. Moreover, vibration of pre/post-buckled sandwich beam with self-deployable shape memory alloy (SMA) core and SMA wires reinforced hybrid composite faces is investigated. The Boyd and Lagoudas SMA constitutive model is utilized in ABAQUS UMAT subroutine. Extensive numerical studies presented for pre-strain, volume fraction, location, time and temperature of heat treatment depends on the properties of SMA fibers, along with core and hybrid composite temperature dependency. As can be seen from results, vibration behaviors, thermal stability and total thickness of self-foldable sandwich structure can be efficiently controlled by adjusting the values of SMA wires volume fraction, pre-strain and core type, respectively. Mechanical properties of SMA are decreased, as a result of increase in heat treatment time and temperature. Increasing heat treatment temperature leads to lower transformation temperatures of SMA. In contrast, higher transformation temperatures are the results of increasing heat treatment time. [ABSTRACT FROM AUTHOR]

The dynamic stability of composite sandwich plates with a smart elastomer layer subjected to an axial periodic load is investigated. A finite element model of the composite sandwich plate with Magnetorheological elastomer (MRE) core is developed. A MRE layer, which its mechanical properties change with the applied magnetic field, is used as a damping layer to improve the stability of the structure. Due to the intrinsic characteristics of the MREs, these materials commonly operate in their pre-yield region. In this region, complex shear modulus is used for these materials. The effect of different parameters such as stacking sequences, boundary conditions, geometry of the sandwich plate, thickness and partial activation of the MRE layer on the damping treatment and stability boundaries is investigated. The presented results show that the application of an MRE layer as a core in the composite sandwich plate changes the stability region of the structure. Therefore, the instability boundaries can be manipulated to achieve the desired dynamic response of the structure. [ABSTRACT FROM AUTHOR]

Abstract In this paper the isogeometric method is used to present a shear refined composite beam model through the concept of dimensional reduction method. A one-dimensional (1D) beam model is extracted from three-dimensional (3D) elasticity problem. The 1D beam model is developed using cross-sectional properties from two-dimensional (2D) beam sectional analysis. The 2D analysis of the cross-section is presented by implementing the transverse shear effects in isogeometric analysis. In beam cross-sectional problem, the influence of linear parameterization is investigated for isogeometric modeling of beam cross-section. Moreover, the effect of delamination on cross-sectional stiffness constants is discussed. Using isogeometric analysis (IGA), less degrees of freedom is needed in contrast to classical finite element method and automatic mesh refinement capability is attained. The present composite beam model eliminates the expensive use of 3D finite element analysis with its high precision and fidelity to 3D problem. [ABSTRACT FROM AUTHOR]

In this paper, cross-sectional analysis of composite beams using a Rayleigh-Ritz-based dimensional reduction method is presented. In dimensional reduction method, the three-dimensional (3D) elasticity problem is reduced to a two-dimensional (2D) cross-sectional analysis which yields cross-sectional stiffness constants. Then a one-dimensional (1D) beam problem, with fidelity to 3D deformation effects, is attained. Using Rayleigh-Ritz method, the cumbersome procedure of mesh generation on beam section is eliminated in contrast to finite element-based cross-sectional analysis. Shear deformation effects and B-spline basis functions in Rayleigh-Ritz-based cross-sectional analysis are considered in this study. Different isotropic and composite beams are examined. Moreover, the effects of considering transverse shear deformation, coupling stiffness constants and honeycomb core for composite thin-walled beams are investigated. Using the present method, a fast and precise tool for analysis of composite beams with arbitrary cross-section geometry and material anisotropy is available for design of composite beam-like structures. [ABSTRACT FROM AUTHOR]

A novel isogeometric-based cross-sectional analysis of composite beams with arbitrary cross-section geometry and a one-dimensional composite beam model is presented via the concept of dimensional reduction method. In dimensional reduction method, three-dimensional beam problem is decomposed into a two-dimensional beam cross-sectional analysis and a one-dimensional beam problem. To achieve this goal, warping displacements should be computed by solving a cross-sectional eigenvalue problem. The cross-sectional analysis is accomplished by spline basis functions to describe unknown warping fields as well as beam cross-section geometry in an isogeometric framework. The present method benefits from the exact geometric definition of beam cross-section, greatly simplifying mesh refinement and better convergence in contrast to classical finite element method. The proposed beam cross-sectional analysis is applied to a variety of beam cross-section configurations with isotropic and anisotropic materials, which show good correlation with the available results in the literature. [ABSTRACT FROM AUTHOR]

Grid structures are extensively used in many engineering structures as an orthotropic layer with at most in-plane anisotropy. In this study, the laminated grids structures are considered. These structures are composed of various numbers of thin composite grid layers. This concept yields to numerous laminated grid configurations with disparate coupling effects, which can be used to tailor the stiffness, compare to conventional grids. In the present study, four known grid patterns with equal weight and thickness constitute the laminated grids. The genetic algorithm (GA) is employed to optimize the stacking sequence and pattern composition of the laminated grid. The buckling load is taken as a fitness function and the pattern and orientation of the grid layer are considered as the design variables. The first-order shear deformation and classical laminated plate theories are considered along with Ritz method to obtain the elastic buckling loads. The optimization results are presented for various boundary conditions and aspect ratios. The results show, using the laminated grid considerably improves the axial buckling load of the plates. Moreover, the plate boundary conditions and aspect ratios play an imperative role in the optimum pattern and stacking sequence of the laminated grid plates. [ABSTRACT FROM AUTHOR]

Free vibration analysis of rotating composite beams with arbitrary cross section is presented. The analysis is based on dimensional reduction method. Contrary to most of the previous studies, which finite element is used to analyze the cross section, the present study examines a simple polynomial based sectional analysis. The three-dimensional (3D) elasticity problem of the composite beam is decomposed into a two-dimensional (2D) cross section analysis and a one-dimensional (1D) beam analysis. In 2D cross-sectional problem in-plane and out-of-plane warpings are calculated by minimizing the energy functional with respect to warping functions. Simple polynomial series are employed to derive the necessary warping functions analytically. Cross sectional properties are determined as a fully populated 4×4 stiffness matrix. Based on a 1D beam potential and kinetic energy, natural frequencies of rotating and non-rotating beams are obtained. The presented approach is applied to isotropic, laminated composite beams as well as thin-walled composite box beams. The effects of fiber angle and rotational speed are investigated for flap and lag bending vibration. The accuracy of the results is validated in comparison with other theories, 3D FEM and experimental data. This procedure, which gives accurate predictions, eliminates the costly use of 3D finite element analysis. [ABSTRACT FROM AUTHOR]

Generally, a grid layer is used as an orthotropic layer to reinforce plates and shells or as an independent structural element. The proposed laminated grid plate is composed of different grid layers with different orientations. Consequently, the grid layers with different fibers, patterns and orientations can be used, resulting in laminates with enhanced stiffness and coupling effects. In the present study, to investigate the efficiency of the laminated grids, the vibration and buckling responses of a conventional and laminated grid plates are compared. The first-order shear deformation plate theory along with Ritz method is used to obtain the buckling load and natural frequencies of the plates. The effectiveness of increasing the number of layers on mechanical responses of the laminated grids is also studied. The analytical results of vibration frequencies are compared and validated by finite element method and experimental analysis of two manufactured grid plates. The results indicate that thoughtful selection of stacking sequences of the laminated grids considerably enhances the response of the laminated grids in comparison with conventional grids. [ABSTRACT FROM AUTHOR]

Generally, a grid layer is used as an orthotropic layer to reinforce plates and shells or as an independent structural element. The proposed laminated grid plate is composed of different grid layers with different orientations. Consequently, the grid layers with different fibers, patterns and orientations can be used, resulting in laminates with enhanced stiffness and coupling effects. In the present study, to investigate the efficiency of the laminated grids, the vibration and buckling responses of a conventional and laminated grid plates are compared. The first-order shear deformation plate theory along with Ritz method is used to obtain the buckling load and natural frequencies of the plates. The effectiveness of increasing the number of layers on mechanical responses of the laminated grids is also studied. The analytical results of vibration frequencies are compared and validated by finite element method and experimental analysis of two manufactured grid plates. The results indicate that thoughtful selection of stacking sequences of the laminated grids considerably enhances the response of the laminated grids in comparison with conventional grids. [ABSTRACT FROM AUTHOR]

This paper tries to analyze the laminated plates with variable cross section, using the Dynamic relaxation method for solving the governing equations of the thin composite plate, obtained from the CPT theory. Comprehensive comparison and parametric studies prove the accuracy and efficiency of the utilized approach with interesting specifications such as fully vector calculations, independency to the lamina scheme (angle and number of plies) and boundary conditions so that the laminated plates with uniform, variable one direction and variable two direction of cross section could be analyzed. Results show that the behaviour of the composite plates depends on both lamina scheme (the stacking sequences and the number of the plies), and the cross section variation of the laminated plate. In this manner, utilizing the laminated plates with variable two direction of cross section could absorb more potential energy in comparison with uniform and variable one direction of cross section, so that they are useful for using in passive control mechanisms in which the kinetic energy should be removed from the structure by transforming to the potential energy. [ABSTRACT FROM AUTHOR]

In this study, a new simple technique called, “smart collocation” is presented. This method is an extension of the collocation method for solving strongly nonlinear boundary value ordinary differential equations. Effects of varying the iteration steps, degree of nonlinearity and position of the collocation points in each sub-interval are investigated. To verify, the calculated results are compared with the bvp4c MATLAB function results. It is shown that, in the case of strongly nonlinear equations, more accurate results can be achieved by moving the position of the collocation points in sub-intervals. For a general problem, based on the degree of nonlinearity, a criterion for selecting appropriate collocation points is obtained. It is shown that varying the position of collocation points or simply smart collocation method can obviously increase accuracy of the solution. [ABSTRACT FROM AUTHOR]

This paper focuses on vibration suppression of frames using an efficient method for determining the sensor/actuator locations. Utilizing the structural dynamics theories, the suitable locations of actuator and sensor are determined based on introducing the magnification factor. This approach is suitable for vibration control of structures with different kinds of degrees of freedom. To verify the validity and efficiency of the proposed scheme, the vibrations of frames are suppressed under various dynamic loads. Results show that the suggested process has suitable ability to use in smart frames so that the vibrations are reduced and damped in few periods of time. [ABSTRACT FROM AUTHOR]

Abstract: The objective of the present study is to enlighten the influence of external electrorheological (ER) dampers on the dynamic behavior of composite laminated plates. Short time response along with electric field depended rheological behavior of ER fluids make these materials attractive for active vibration control of structures. To demonstrate the effect of ER damper on dynamic response of the composite plate, the finite element formulation based on the first order shear deformation theory (FSDT) is obtained for laminated plates. Moreover, the Bingham plastic model, which presents the post-yield behavior of the ER material, is used to model the ER fluid. Several numerical results are presented and effects of imperative parameters are discussed. It is shown that parameters such as applied voltage, controlled electric field, radius and initial gap of the electrodes, position of the ER damper and the stacking sequences of the composite plate have considerable effect on the vibration suppression time of the plate. [Copyright &y& Elsevier]

In this paper, torsional analysis of hollow bars with specially shaped non-circular cross-sections is presented. The well-known formulation of the torsion problem in complex variable theory is used to obtain an expression for shear stresses, angle of twist and cross-sectional warping. The most important part of the solution of the torsion problem here is to obtain an appropriate closed-form conformal mapping for specially shaped cross-sections. The obtained mapping is used to achieve a solution for torsion problem of bars with specially shaped hollow cross-section. Finally, the calculated results are compared with the finite-element method solution. The presented solution is capable of accurately predicting the angle of twist, warping, and shear stress in the studied hollow bars. [ABSTRACT FROM PUBLISHER]

In this study, the flutter pressure of delaminated composite beam-plates subjected to supersonic flow is investigated using similitude theory. An analytical investigation based on the direct use of the governing equations of the systems is undertaken to derive the necessary scaling laws and similarity conditions. The method presented herein has already been shown to be effective in the design of scaled down models for buckling and vibration response of laminated composite shells and panels. In this study, the flutter pressures of the prototypes are predicted by projecting the flutter pressure of the model using the derived scaling law. Based on the result of this study, for flutter of delaminated composite beam-plates, based on structural similitude, set of scaling laws can be found, which are used to develop design rules for small-scale models. For prototypes with the same material properties and stacking sequence as the prototype, distorted models with different delamination length and depth than those of the prototype can predict the behavior of the prototypes, accurately. [ABSTRACT FROM AUTHOR]

This article focuses on dynamic stability of smart sandwich beams resting on Winkler elastic foundation subjected to harmonic axial loads. To increase the dynamic buckling load and the stability region of the beam, an electro-rheological layer is adhered as a core. The finite element method is employed to derive a three layer smart sandwich beam element. By inspecting dynamic response of the beam in different load amplitudes, critical dynamic loads are calculated. Parametric study is done to investigate effects of various parameters such as beam geometry, foundation stiffness, static load, applied voltage and properties of core layer on critical dynamic loads and stability regions of the beam. This study indicates that by applying electric field to the electro-rheological core, dynamic critical load and consequently, dynamic stability of the beam increase efficiently. Furthermore, the elastic foundation reduces the unstable region and increases the critical dynamic load of the smart beam. Proper use of these parameters makes the beam less sensitive to axial harmonic loading by relocating the instability region. [ABSTRACT FROM AUTHOR]

In this article, an effort has been made to deal with stability analysis of a smart sandwich beam with cross-ply faces and ER core. An ER layer is adhered to the laminated composite beam to increase dynamic stability of the beam. Bingham’s model is applied to model dynamic behavior of ER layer. A smart beam element is derived for the sandwich beam and finite element modeling is carried out. Transient response of the beam to an initial excitation is calculated using direct integration method. By analyzing the dynamic responses of the beam in different load amplitudes, critical loads and stability regions are obtained. Parametric study has been done and effects of various parameters such as the electric field, stacking sequence of the layers, and thickness ratio of elastic faces on static and dynamic stability of the beam are investigated. Obtained results show that stacking sequence and thickness ratio of elastic faces affects both static and dynamic stability of the beam. On the other hand, ER layer affects damping properties of structures as a result of which only dynamic stability of the beam is improved. [ABSTRACT FROM PUBLISHER]

The dynamic buckling of the patched perforated cylindrical panels, subjected to axial impact load, is investigated. Effects of various parameters such as load time duration, sector angle, cutout size, and thickness of the cylindrical panel are investigated. Furthermore, the effectiveness of the application of single or double-sided composite patches in enhancement of dynamic load carrying capacity of the perforated panels is presented. Due to complexity, material anisotropy, and discontinuity in geometry involved in the dynamic analysis of perforated/repaired panels, closed-form solutions are practically unobtainable. Numerical studies using commercial finite element code is used for the analyses. The results presented herein indicate that patches with a different number of plies and stacking sequences can be found, which improve the dynamic buckling load of the perforated panels. [ABSTRACT FROM PUBLISHER]

Abstract: The main objective of this study is to demonstrate the applicability of similitude theory in designing scaled down models to predict the flutter pressure of delaminated composite beam-plate subjected to supersonic airflow. The linear plate theory is used for structural modeling, and linear piston theory is used for aerodynamic modeling. In this study, we consider only the procedure that is based on the direct use of the governing equations. Distorted models with different fiber orientation, delamination size, and axial position than those of prototype are studied. Results show that a set of scaling models can be found which can predict the flutter pressure of delaminated beam-plate accurately. [Copyright &y& Elsevier]

Abstract: This study describes the establishment of the necessary similarity conditions for dynamic aeroelastic stability of laminated composite plates. An analytical investigation based on the direct use of the governing equations of the systems is undertaken to derive the necessary scaling laws and similarity conditions. The method presented herein has already been shown to be effective in the design of scaled down models for buckling and vibration response of laminated composite shells and panels. In this study, the flutter speeds of the prototypes are predicted by projecting the flutter speed of the model using the derived scaling law. The results presented herein, indicate that, for flutter of composite plates, based on structural similitude, a set of scaling laws can be found, which are used to develop design rules for small scale models. Models with different material properties, thickness, fiber orientation, Mach number, aspect ratio, and number of plies than those of the prototype can predict the flutter behavior of the prototype with good accuracy. [ABSTRACT FROM AUTHOR]

Perforated plates and shells with variously shaped cutout are often used in engineering structures. Despite the importance of the effects of cutout on the load-bearing capacity and stress concentration of such plates little research has focused on stress analysis of plates with special shaped cutout. This study investigates problems associated with the maximum stresses in perforated composite plates with quasi-square shaped cutouts. Analytical solution based on Lekhnitskii's theory of anisotropic plate is utilized for stress analysis of composite plates with central square shaped cutout. The solution is capable of considering large variety of cutout shapes and loading conditions analytically. Parametric studies were conducted to investigate the effects of variation in cutout bluntness and orientation, material properties, and loading direction on the location and the value of the maximum stress in a flat composite plate subjected uni-axial tension load. Based on results presented herein, the maximum normalized stress of perforated composite plates can be significantly changed by using proper combination of material properties, fiber orientation, loading angle, cutout bluntness, and orientation. [ABSTRACT FROM AUTHOR]

The performance of damaged metallic plates reinforced with fiber-reinforced polymer composite materials (composite patches) is presented in this study. A square aluminum plate with a central cutout is considered as a damaged structural element. Numerical studies using commercial finite element code were conducted to investigate the effects of variation in patch lamination parameters on flutter velocity of the repaired plates. The various laminate parameters such as fiber angles and stacking sequences are considered in this study. The results presented herein indicate that, for flutter pressure of a repaired metallic plate with central cutout, a set of laminated composite patches with different number of plies and stacking sequences can be found, which improve flutter pressure of damaged plates. [ABSTRACT FROM AUTHOR]

The performance of damaged metallic plates reinforced with fiber-reinforced polymer composite materials (composite patches) are presented in this study. A square aluminum plate with a central circular cutout is considered as a damaged structural element. Numerical studies using commercial finite element code were conducted to investigate the effects of variation in patch geometries and lamination parameters on buckling responses of repaired plates. The varying laminate parameters, such as fiber angles and stacking sequences, are considered in this study. A quantitative measure for the effectiveness of the composite patches is taken to be the relative change in buckling loads of the reinforced plates compared to that of the unreinforced one. The results presented herein indicated that, for buckling response of a repaired metallic plate with central cutout, a set of laminated composite patches with different number of plies and stacking sequences can be found which improve the load-carrying capacity of damaged plates. [ABSTRACT FROM AUTHOR]

Abstract: This study investigates the applicability of scaled models for predicting the buckling behavior of delaminated composites. Such a study is important since it provides the necessary scaling laws, and the factors which affect the accuracy of the scale models. Employment of similitude theory to establish similarity among structural systems can save considerable expense and time, provided that the proper scaling laws are found and validated. In this study a number of parametric studies are performed. The limitations and acceptable intervals of all parameters and corresponding scale factors are investigated. Particular emphasis is placed on the case of delamination buckling of orthotropic plates. Both complete and partial similarities are discussed. This study indicates that models with a different delamination size, depth and number of delaminations than those of the prototype are capable of predicting buckling loads of the prototypes with good accuracy. [Copyright &y& Elsevier]

This paper is intended to investigate the static behavior of pre-twisted composite beams using an isogeometric-based cross-sectional analysis. The three-dimensional pre-twisted beam problem is decomposed into a two-dimensional cross-sectional analysis and a one-dimensional beam model. The cross-sectional analysis obtains stiffness constants by considering three-dimensional warping deformation effects. The influence of pre-twist ratio is investigated on the stiffness constants and one-dimensional deformations of isotropic beams, composite strips and box-beams. Inconsistencies in results of pre-twisted composite beam theories in the literature are addressed and discussed. The present method eliminates the costly use of three-dimensional finite element analysis in the initial design steps. • An IGA-based cross-sectional analysis of pre-twisted composite beams is presented. • The effect of pre-twist is investigated on stiffness constants and 1D deformations. • Using IGA, automatic mesh refinement and good convergence behavior are attained. • Inconsistencies in results of pre-twisted beam theories in literature are discussed. [ABSTRACT FROM AUTHOR]

An experimental study on the natural frequencies and damping properties of hybrid composite beams and plates are presented in this paper. Hybrid composites consist of a matrix material along with both nano-fillers and micro fibers. In this research, carbon nanotube (CNT) is used as nano-filler. Epoxy, CNT/epoxy, glass/epoxy, CNT/glass/epoxy, carbon/epoxy and CNT/carbon/epoxy beam-shaped specimens are fabricated. Free vibration analysis of cantilever beams is examined in order to characterize the dynamic behavior of the specimens. 9.4% increase in the fundamental frequency and 12.3% decrease in the damping ratio of the CNT/glass/epoxy beam are observed with respect to those of the glass/epoxy beam specimen. Further, it is observed that CNT/carbon/epoxy beam has degraded fundamental frequency (13.9%) and enhanced damping ratio (31.5%) in comparison with those of carbon/epoxy beam specimen. Moreover, the first bending natural frequencies of the glass/epoxy, CNT/glass/epoxy, carbon/epoxy and CNT/carbon/epoxy plates are obtained experimentally. Plates with all free edges (FFFF) and plates with one edge clamped (CFFF) are investigated. Finite element models confirm the results obtained. Furthermore, the effects of the interfacial adhesion between the CNT/epoxy matrix and micro fibers on the damping properties of the laminated composites are discussed using the obtained results and the scanning electron microscopy (SEM) images. [ABSTRACT FROM AUTHOR]

This study deals with free vibration analysis of integrated and non-integrated corrugated core sandwich panels with rectangular core together with free vibration analysis of integrated corrugated core sandwich panels with hat-type and triangle core. Bonding of the core to skin in non-integrated sandwich panels was achieved by resin, while in the integrated sandwich panels that were reinforced with 3-D weft-knitted fabric bonding was achieved using yarns and resin. Results revealed that the integrated structures have higher natural frequency than the non-integrated structures. It was also found that the natural frequency of the triangular-core sandwich panels and the rectangular-core sandwich panels was the highest and the lowest, respectively. It was established that weft-knitting fabric technology is suitable for the production of both integrated and non-integrated corrugated core sandwich panels with a high degree of similarities in terms of geometry, weight, and characteristics. [ABSTRACT FROM AUTHOR]

This study presents a new method for strengthening the circular reinforced concrete (RC) column to foundation connections with shape memory alloy (SMA) bars and carbon fiber reinforced polymer (CFRP) sheets. In the experimental part of the study, three specimens of RC column-foundation connections were cast and tested. One specimen was used as the reference specimen without strengthening. Two other specimens were strengthened with longitudinal SMA bars and CFRP sheets. These specimens were under a constant axial compressive load and cyclic lateral displacements, simultaneously. Next, initial stiffness, energy dissipation capacity, lateral load capacity, ductility, and residual displacement of the specimens were investigated. Due to the superelastic behavior of SMA bars, the residual displacement of column-foundation connections was considerably less than that of the reference specimen. Compared to the reference specimen, the SMA-strengthened and SMA-CFRP-strengthened connections recovered 71.59% and 76.57% of the residual displacement. Therefore, SMA bars were able to recover residual displacements under cyclic loading. Also, the combination of the SMA bars with CFRP sheet was a promising solution for enhancing the amount of the energy dissipation, lateral load capacity, initial stiffness, and ductility parameters. Compared to the reference specimen, the energy dissipation, lateral load capacity, initial stiffness, and ductility ratio parameters of SMA-CFRP-strengthened connection increased about 43.45%, 76.20%, 81.69%, and 242.45%, respectively. In the numerical part of the study, a subroutine was applied for modeling the SMA materials. For the analysis, this subroutine was linked with ABAQUS software. The numerical results showed a close correlation with the experimental results. [ABSTRACT FROM AUTHOR]

This article aims to evaluate the effect of core geometry on flexural stiffness and transverse shear rigidity of corrugated core sandwich panels both experimentally and numerically. Using vacuum‐assisted resin transfer molding (VARTM) method, three composite sandwich panels reinforced with 3D weft knitted spacer fabric with rectangular, hat‐type (trapezoidal) and triangular cross‐sectional geometries were produced. In order to eliminate weight variation among the produced sandwich panel samples, the unit cell dimensions, core wall to skin angle, and the yarn count used to knit the core wall were carefully chosen. Results pointed to existence of statistically significant difference between the load‐carrying capacity and transverse shear rigidity in the direction of corrugation of the structures. It was concluded that triangular and rectangular structures have the highest and lowest load‐carrying capacity, transverse shear rigidity, and core shear modulus in the direction of corrugation, respectively. [ABSTRACT FROM AUTHOR]