Experimental and finite element studies on free vibration of cylindrical skew panels

Composite laminates are being widely used in engineering industry primarily due to their high strength-to-weight ratio. Considerable research has been carried out to understand the static and dynamic behaviour of laminated composite plates. There is much demand for developing efficient finite element codes which can predict the dynamic responses of laminated structures at affordable computational cost. In this paper a nine node isoparametric plate bending element has been used for free vibration analysis of laminated composite plate. The first-order shear deformation theory (FSDT) has been incorporated in the element formulation. Composite plates with different side-to-thickness ratio (a/h), ply orientations and number of layers have been analysed. Based on comparison with literature data, we propose that the present formulation is capable of yielding highly accurate results. Laminated composites with central cutouts are also studied. Novel data is reported for skew laminated composites. It is found that the natural frequency increases with the increase in skew angle (α) and decreases with increase in aspect ratio (b/a) and thickness (h).

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“…Also the natural frequencies increase with an increase in the skew angle. These findings are in excellent agreement with Srinivasa et al [30].…”

Section: Anti-symmetric Skew Laminatessupporting

confidence: 93%

Free Vibration Analysis of Laminated Composites by a Nine Node Isoparametric Plate Bending Element

Kalita

Ramachandran

Raichurkar

et al. 2016

Advanced Composites Letters

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“…Lanczos method was used in the present study as it combines the best features of the other methods and computes accurate eigenvalues and eigenvectors [22,26]. Table 2 shows the results of validation.…”

Section: Finite Element Methodsmentioning

confidence: 99%

“…The CQUAD8 element is a eight-node isoparametric shell element having six degrees of freedom / node (translational (u, v, w) and rotational (θx, θy, θz)). Both the elements take into account the shear deformations [20][21][22][23][24][25][26].…”

Section: Finite Element Methodsmentioning

confidence: 99%

Buckling Behaviour of Cylindrical Panels

Ashok

Srinivasa²,

Suresh³

et al. 2015

Nonlinear Engineering

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Experimental studies were made on isotropic cylindrical panels made of Aluminum 7075-T6 under uniaxial compression. The experimental values of the critical buckling load were determined using four di erent methods. The critical buckling load was also determined using MSC/NASTRAN and CQUAD8 nite element. The experimental values of the critical buckling load obtained by di erent methods were compared with the nite element solution. The e ects of the panel angle, panel length and panel thickness on the critical buckling load of isotropic cylindrical panels made of Aluminum 7075-T6 were studied. It is found that the Method III (based on a plot of applied load versus average axial strain) yields the highest value for critical buckling load and Method II (based on a plot of applied load versus square of out-of-planede ection) the lowest value for critical buckling load. The experimental values given by Method III are seen to be closest to the nite element solution. Critical buckling load increases monotonically as panel angle increases.

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“…But the analysis of stiffened shells with cutout for higher modes is scanty in the literature. Some studies [24,25] also reported the mode frequency analysis of laminated spherical and cylindrical shells. However, the analysis of stiffened hypar shells with cutout for higher modes is yet to be reported in literature.…”

Section: Introductionmentioning

confidence: 99%

Mode frequency analysis of antisymmetric angle-ply laminated composite stiffened hypar shell with cutout

Chaudhuri¹,

Mitra

Sahoo³

2019

Mechanics and Mechanical Engineering

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This article deals with finite element method for the analysis of antisymmetric angle-ply laminated composite hypar shells (hyperbolic paraboloid bounded by straight edges) that applies an eight-noded isoparametric shell element and a three-noded beam element to study the mode-frequency analysis of stiffened shell with cutout. Two-, 4-, and 10-layered antisymmetric angle-ply laminations with different lamination angles are considered. Among these, 10-layer antisymmetric angle-ply shells are considered for elaborate study. The shells have different boundary conditions along its four edges. The formulation is based on the first-order shear deformation theory. The reduced method of eigen value solution is chosen for the undamped free vibration analysis. The first five modes of natural frequency are presented. The numerical studies are conducted to determine the effects of width-to-thickness ratio (b/h), degree of orthotropy (E11/E22), and fiber orientation angle (θ) on the nondimensional natural frequency. The results reveal that free vibration behavior mainly depends on the number of boundary constraints rather than other parametric variations such as change in fiber orientation angle and increase in degree of orthotropy and width-to-thickness ratio.

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Experimental and finite element studies on free vibration of cylindrical skew panels

Cited by 10 publications

References 15 publications

Free Vibration Analysis of Laminated Composites by a Nine Node Isoparametric Plate Bending Element

Free Vibration Analysis of Laminated Composites by a Nine Node Isoparametric Plate Bending Element

Buckling Behaviour of Cylindrical Panels

Mode frequency analysis of antisymmetric angle-ply laminated composite stiffened hypar shell with cutout

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