Vibrational analyses of stiffened and unstiffened composite plates subjected to in-plane loads

Attaf, B; Hollaway, L.

doi:10.1016/0010-4361(90)90003-f

Cited by 21 publications

(9 citation statements)

References 4 publications

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“…2, for the first three vibration modes of the thin plate, the experimental curves bear almost no resemblance to the theoretical curves. Other researchers who have dealt with the subject of the correlation between the vibration and the stability problem of structures are Plaut and Johnson [6], Plaut and Virgin [7], Singer [8,9], Jubb et al [10] and Attaf and Hollaway [11]. Some of these workers came to similar conclusions as Lurie and Ilanko.…”

Section: Literature Reviewmentioning

confidence: 67%

Modal parameter identification of a compression-loaded CFRP stiffened plate and correlation with its buckling behaviour

Chaves-Vargas

Dafnis

Reimerdes

2015

Progress in Aerospace Sciences

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Section: Literature Reviewmentioning

confidence: 67%

Modal parameter identification of a compression-loaded CFRP stiffened plate and correlation with its buckling behaviour

Chaves-Vargas

Dafnis

Reimerdes

2015

Progress in Aerospace Sciences

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“…The stiffener laminations are perpendicular to the plane of the plate. 22 The thickness of the plate is 2.208 mm. The breadth and height of the stiffener are 6 and 12 mm, respectively.The typicalmaterial parametersare E1 = E2 = 7 GPa, G12 = G13 = G23 = 2.6 GPa, P R12 = 0.345, q = 1504.2 kg/m 2 .…”

Section: Problem 1: Uniaxially Stiffened Clamped Composite Plate Withmentioning

confidence: 99%

Estimation of Layerwise Elastic Parameters of Stiffened Composite Plates

Chakraborty

Mukhopadhyay

2000

AIAA Journal

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For the rst time, an investigation of stiffened and unstiffened multilayered composite plates has been conducted to determine the material property parameters of the plate as well as the stiffener from numerically simulated experimental modal data and nite element predictions, using model updating techniques. The problem is formulated as a global minimization of the error function, de ned by the difference in undamped eigenvalues as well as mode shapes, as predicted from the nite element modeling compared to that obtained experimentally. The parameter estimation problem is solved using an iterative gradient-based minimization algorithm, which can start from any randomly selected set of initial parameters. The position, physical properties, and orientation of stiffeners create considerable variations in the modal properties as compared to the bare plates of similar construction. This makes each of the stiffened plate problems rather unique. A few simulated examples are presented, and the methodology is found to be robust, even in the presence of random noise. Nomenclaturea = amplitude of noise boundl(i ) = lower bound of the variable boundu(i ) = upper bound of the variable E = Young's modulus of a lamina E T = total error term in the objective function E1 = Young's modulus of a lamina of the plate in the longitudinal material direction E2 = Young's modulus of a lamina of the plate in transverse material direction E S1 = Young's modulus of the lamina of the stiffener in longitudinal material direction E S2 = Young's modulus of the lamina of the stiffener in transverse material direction E x , E u , E p = error terms for frequency, mode shape, and internal penalty, respectively G12, G13, G23 = shear modulus of the lamina of the plate G S12 = in-plane shear modulus of the lamina of the stiffener M = number of measured modes ncons = number of parameters with constraints nused = number of modes considered P L i = lower bound of the i th parameter P U i = upper bound of the i th parameter P ¤ i = value of the i th parameter P R12= in-plane Poisson's ratio of the lamina of the plate P S12 = in-plane Poisson's ratio of the lamina of the stiffener r = uniformly distributed sequence of random numbers between ¡ 1 and +1 rr(i ) = constant for evaluating internal penalty W x , W u , W p = weighting factors of frequency, mode shape, and internal penalty, respectively X = noise-free reference data X ¤ = noisy data (frequency or component of eigenvector) x(i ) = i th parameter g = deterministic design allowable

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“…Using the isoparametric shape function the accelerations at any point in the reference axis of the plate 8 can be expressed in terms of the nodal accelerations 8 =N r l£r r = 1. .. n (22) where N r is the shape function for the node r, Is is an identity matrix of eighth order, 8 r are the nodal accelerations and n is the number of nodes in the element. The inertial forces at any point within the stiffener can be obtained by multiplying the accelerations at that point by density…”

Section: Consistent Mass Matrixmentioning

confidence: 99%

“…The introduction of the shear correction factor is not necessary for this element. The free vibration of composite stiffened plates subjected to inplane compressive loads has been presented by Attaf and Hollaway' 22 '. In the analytical study the plate and the blade stiffener element have been modelled using S4R element of the ABAQUS computer code.…”

Section: Introductionmentioning

confidence: 99%

Free vibration of laminated beams and stiffened plates using a high-order element

Mukherjee

1991

Aeronaut. j.

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Free vibration analysis of laminated composite beams, plates and stiffened plates using the finite element method has been presented. To give due importance to the shear deformation in composite materials, a high-order element which considers the quadratic variation of shear strain along the thickness of the element has been developed. The element has been developed using the quadratic isoparametric shape functions. Therefore, it can accommodate curved boundaries. Moreover, the stiffener element can have an arbitrary planform and it need not pass through any nodal point. The stiffener element has been developed in such a fashion to make the mesh division free from the location of the stiffener. This is extremely advantageous for optimisation of the path of the stiffener in a stiffened plated structure, while it is not necessary to modify the mesh division whenever the stiffener path is modified. Two different shape functions — the eight-node Serendipity and the nine-node Lagrangian — have been employed and a comparison between their performances has been presented. Two schemes for the generation of mass matrix, namely the lumped mass scheme and the consistent mass scheme, have been developed. The elements have been implemented in the ASKA element library and they can be used along with any standard ASKA element.

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Vibrational analyses of stiffened and unstiffened composite plates subjected to in-plane loads

Cited by 21 publications

References 4 publications

Modal parameter identification of a compression-loaded CFRP stiffened plate and correlation with its buckling behaviour

Modal parameter identification of a compression-loaded CFRP stiffened plate and correlation with its buckling behaviour

Estimation of Layerwise Elastic Parameters of Stiffened Composite Plates

Free vibration of laminated beams and stiffened plates using a high-order element

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