Forced nonlinear vibration of laminated composite plates with random material properties

Onkar, Amit Kumar; Yadav, D.

doi:10.1016/j.compstruct.2004.08.037

Cited by 46 publications

(17 citation statements)

References 20 publications

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“…Most of the studies on uncertainty analysis of composite structures generally consider E 1 , E 2 , G 12 and 12 as statistically independent random variables and assume a coefficient of variation (c.o.v.) of 5 to 10% for each of these properties [3][4][5][6]. Experimental results for scattering in E 1 , E 2 , and 12 of a graphite/epoxy composite material and their possible distributions are given in [1].…”

Section: Stochastic Cross-sectional Stiffness Valuesmentioning

confidence: 98%

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Aeroelastic Response of Composite Helicopter Rotor with Random Material Properties

Murugan

Ganguli

Harursampath

2008

Journal of Aircraft

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This study investigates the effect of uncertainty in composite material properties on the cross-sectional stiffness properties, natural frequencies, and aeroelastic responses of a composite helicopter rotor blade. The elastic moduli and Poisson's ratio of the composite material are considered as random variables with a coefficient of variation of around 4%, which was taken from published experimental work. An analytical box beam model is used for evaluating blade cross-sectional properties. Aeroelastic analysis based on finite elements in space and time is used to evaluate the helicopter rotor blade response in forward flight. The stochastic cross-sectional and aeroelastic analyses are carried out with Monte Carlo simulations. It is found that the blade cross-sectional stiffness matrix elements show a coefficient of variation of about 6%. The nonrotating rotor blade natural frequencies show a coefficient of variation of around 3%. The impact of material uncertainty on rotating natural frequencies varies from that on nonrotating blade frequencies because of centrifugal stiffening. The propagation of material uncertainty into aeroelastic response causes large deviations, particularly in the higher-harmonic components that are critical for the accurate prediction of helicopter blade loads and vibration. The numerical results clearly show the need to consider randomness of composite material properties in the helicopter aeroelastic analysis.

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Section: Stochastic Cross-sectional Stiffness Valuesmentioning

confidence: 98%

“…The nominal material properties of composites used in the structural design process are uncertain because of manufacturing tolerances and lack of precise experimental data [1][2][3][4][5][6]. Such an imprecision in the material properties can substantially influence the response of aircraft structures [7,8].…”

Section: Introductionmentioning

confidence: 98%

Aeroelastic Response of Composite Helicopter Rotor with Random Material Properties

Murugan

Ganguli

Harursampath

2008

Journal of Aircraft

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“…A few literatures are available on the nonlinear response of composite plates with uncertain material properties to deterministic and random excitation [22][23][24][25][26][27][28]. Onkar and Yadav [22] presented the second-order statistics of static response for a composite plate with random material properties under transverse random loading.…”

Section: Introductionmentioning

confidence: 99%

“…They used a C 0 nonlinear finite element model based on the HSDT in the von Karman sense in conjunction with the FOPT. Onkar and Yadav [25,26] incorporated the nonlinear effects for free vibration analysis in the random environment based on the CLT. The study analyzed a composite flat plate with random material properties with random external loading.…”

Section: Introductionmentioning

confidence: 99%

Static Response of Geometrically Nonlinear Laminated Composite Plates Having Uncertain Material Properties

Dash

Singh

2014

Mechanics of Advanced Materials and Structures

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The effect of uncertainty in material properties on the transverse bending of laminated composite plate is investigated. The transverse shear and large rotations have been included in the system equation in the framework of higher order shear deformation theory. The analysis uses Green-Lagrange nonlinear strain displacement equations to model geometric nonlinearity. The stochastic finite element analysis is performed using a direct iteration approach to handle deterministic geometric nonlinearity and perturbation approach to handle the randomness in the material properties. Mean and variance of the transverse deflection have been obtained by employing a C 0 isoparametric nonlinear finite element model.

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“…Locke [33] presented the thermally buckled and vibration analysis for large deflection response using iterative techniques and method of linearization. Onkar et al [34] presented the generalized force nonlinear vibration of laminated composite plate with random material properties using classical plate theory (CLT) combined with FOPT. Kitipornchai et al [35] studied the vibration composed by the third order shear deformation theory with random material effect using FOPT incorporating mixed type and semi analytical approach to derive the standard eigenvalue problem.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear free vibration analysis of elastically supported carbon nanotube-reinforced composite beam with the thermal environment in non-deterministic framework

Chaudhari¹,

Shegokar²,

Lal

2017

Curved and Layered Structures

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This paper deals with the investigation of nonlinear free vibration behavior of elastically supported carbon nanotube reinforced composite (CNTRC) beam subjected to thermal loading with random system properties. Material properties of each constituent's material, volume fraction exponent and foundation parameters are considered as uncorrelated Gaussian random input variables. The beam is supported by a Pasternak foundation with Winkler cubic nonlinearity. The higher order shear deformation theory (HSDT) with von-Karman nonlinearity is used to formulate the governing equation using Hamilton principle. Convergence and validation study is carried out through the comparison with the available results in the literature for authenticity and accuracy of the present approach used in the analysis. First order perturbation technique (FOPT),Second order perturbation technique (SOPT) and Monte Carlo simulation (MCS) methods are employed to investigate the effect of geometric configuration, volume fraction exponent, foundation parameters, distribution of reinforcement and thermal loading on nonlinear vibration characteristics CNTRC beam.The present work signifies the accurate analysis of vibrational behaviour influences by different random variables. Results are presented in terms of mean, variance (COV) and probability density function (PDF) for various aforementioned parameters.

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Forced nonlinear vibration of laminated composite plates with random material properties

Cited by 46 publications

References 20 publications

Aeroelastic Response of Composite Helicopter Rotor with Random Material Properties

Aeroelastic Response of Composite Helicopter Rotor with Random Material Properties

Static Response of Geometrically Nonlinear Laminated Composite Plates Having Uncertain Material Properties

Nonlinear free vibration analysis of elastically supported carbon nanotube-reinforced composite beam with the thermal environment in non-deterministic framework

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