Geometrically nonlinear dynamic analysis of laminated composite plate using a nonpolynomial shear deformation theory

Thakur, Babu Ranjan; Verma, Seema; Singh, B.N.; Maiti, Dipak Kumar

doi:10.1016/j.ijnonlinmec.2020.103635

Cited by 18 publications

(2 citation statements)

References 63 publications

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“…This formula can be used to calculate the bending and torsion problems of composite laminates well, and the calculation accuracy is in good agreement with the experimental data. Thakur et al [26] proposed a finite element model of C 0 laminated plates, which used von Karman and green-Lagrangian strain-displacement relation to simulate geometric nonlinearity and then derived the nonlinear motion governing equation by using Hamiltonian principle. Finally, the Newton-Raphson method was used to solve the problem.…”

Section: Introductionmentioning

confidence: 99%

Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Wang

Ren

et al. 2021

International Journal of Aerospace Engineering

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In this paper, in order to understand the influence of the unbalanced coefficient of composite laminates on the static aeroelasticity of high aspect wings, a series of numerical simulation calculations were carried out, and this work wants to provide some reference for the structural design of aircraft. Considering the influence of geometric nonlinearity, the unidirectional fluid-solid coupling calculation method based on loose coupling is used to control the change of unbalanced coefficient of laminates on the basis of layering angle, layering thickness, and layering region, so as to observe the changes caused to the wings. The relationship between the unbalanced coefficient and the constant thickness layup and the variable thickness layup with 0° and ±45° layup angles was studied, respectively. Then, the layup angle of 90° was added to study the influence of the unbalanced coefficient on the static aeroelasticity of the wing structure with the change of the layup angle and the different choice of layup region. The results show that the deformation is the smallest when the unbalanced coefficient is 0.5, and the deformation trend is evenly distributed along both sides when the unbalanced coefficient is 0.5. When the unbalanced coefficient is changed, adding the 90° layup angle can significantly reduce the overall deformation of the wing and show different sensitivity characteristics to different layup areas. The increase of the unbalanced coefficient makes the chordal displacement gradually change from linear distribution to nonlinear distribution along the spread direction, and the displacement will gradually decrease.

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Section: Introductionmentioning

confidence: 99%

Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Wang

Ren

et al. 2021

International Journal of Aerospace Engineering

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“…To evaluate the nonlinear dynamics of the laminated composite plates reinforced with graphene, bifurcation diagrams, waveform graphs, and phase plane plots have been used. Thakur et al [24] adapted a computationally efficient C o FE model in combination of the nonpolynomial shear deformation theory (NPSDT) for investigation of forced vibrational behaviour of composite laminated plates.…”

Section: Introductionmentioning

confidence: 99%

Influence of Fiber Angle on Steady-State Response of Laminated Composite Rectangular Plates

Saood¹,

Khan

Equbal³

et al. 2022

Materials

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Significant advances in the field of composite structures continue to be made on a variety of fronts, including theoretical studies based on advances in structural theory kinematics and computer models of structural elements employing advanced theories and unique formulations. Plate vibration is a persistently interesting subject owing to its wider usage as a structural component in the industry. The current study was carried out using the Co continuous eight-noded quadrilateral shear-flexible element having five nodal degrees of freedom, which is ground on first-order shear deformation theory (FSDT). For small strain and sufficiently large deformation, the geometric nonlinearity is integrated using the Von Kármán assumption. The governing equations in the time domain are solved employing the modified shooting technique along with an arc-length and pseudo-arc-length continuation strategy. This work explored the effect of fiber angle on the steady-state nonlinear forced vibration response. To explain hardening nonlinearity, the strain and stress fluctuation throughout the thickness for a rectangular laminated composite plate is determined. The cyclic fluctuation of the steady-state nonlinear normal stress during a time period at the centre of the top/bottom surfaces is also provided at the forcing frequency ratio of peak amplitude in a nonlinear response. Because of the variation in restoring forces, the frequency spectra for all fiber angle orientations show significantly enhanced harmonic participation in addition to the fundamental harmonic.

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Random vibration responses and reliability analyses of thin plates with geometric nonlinearity via direct probability integral method

Liu

Jian

et al. 2023

Nonlinear Dyn

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Geometrically nonlinear dynamic analysis of laminated composite plate using a nonpolynomial shear deformation theory

Cited by 18 publications

References 63 publications

Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Influence of Fiber Angle on Steady-State Response of Laminated Composite Rectangular Plates

Random vibration responses and reliability analyses of thin plates with geometric nonlinearity via direct probability integral method

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