Free Vibration Analysis of Delaminated Composite Plate Using 3D Degenerated Element

Tiwari, Pratik; Barman, Swarup K.; Maiti, Dipak Kumar; Maity, Damodar

doi:10.1061/(asce)as.1943-5525.0001053

Cited by 18 publications

(7 citation statements)

References 32 publications

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“…The mechanical properties of the composite are 71 : E 11 = 6.125 × 10 9 N / m 2 , E 22 = 5.421 × 10 9 N / m 2 , G 12 = G 13 = 2.79 × 10 9 N / m 2 , G 23 = 1.395 × 10 9 N / m 2 , υ 12 = 0.17, ρ = 1400 kg / m 3 . The natural frequencies of the first-five modes for the delaminated plates using the present FE model are well-matched with the experimental and numerical results of, 58 and 61 as presented in Table 5. Further, a six-layered composite plate subjected to aerodynamic forces in a wind tunnel test set-up is considered for aeroelastic analysis.…”

Section: Resultssupporting

confidence: 77%

“…The combined effect of stochasticity and delamination significantly influences the dynamic behaviour of the composite plate. 60 An efficient 3-dimensional degenerated element 61 based finite element model is proposed for the delamination analysis of composite plates. The presence of delamination can have a positive and negative influence on the flutter and divergence velocity.…”

Section: Introductionmentioning

confidence: 99%

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Aeroelastic control of delaminated variable angle tow laminated composite plate using piezoelectric patches

Sharma

Swain

Maiti

2022

Journal of Composite Materials

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The free vibration and aeroelastic analysis of variable angle tow (VAT) laminated composite plate bonded with discrete piezoelectric patches are considered for investigation. A finite element (FE) model is developed using eight noded isoparametric elements to study the impact of delamination size and location on the dynamic response of smart VAT laminated plates. For aeroelastic analysis, the FE model is coupled with MSC. Nastran through Direct Matrix Abstraction Program (DMAP) and the structural parameters obtained with the FE model are supplied to MSC. Nastran solver to generate aerodynamic force matrix using Doublet Lattice Method (DLM). Various parametric studies are performed to find the most critical location of the delamination that severely affects vibration and flutter characteristics. The results showed that the delamination near the leading edge which faces free stream wind is found to be the most critical for the dynamic aeroelastic failure of structures. Further, the most effective location of the piezoelectric patches is identified to enhance the aeroelastic boundary of smart delaminated VAT composite plates using active displacement and velocity feedback gains.

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Section: Resultssupporting

confidence: 77%

Section: Introductionmentioning

confidence: 99%

Aeroelastic control of delaminated variable angle tow laminated composite plate using piezoelectric patches

Sharma

Swain

Maiti

2022

Journal of Composite Materials

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“…A mathematical model for analyzing delaminated plates is developed using three-dimensional (3D) degenerated elements in the work of Tiwari et al [79]. The elements are introduced, applying the degenerated solid approach based on the Reissner-Mindlin assumptions.…”

Section: Delamination Of the Buckled Platementioning

confidence: 99%

Mathematical Models with Buckling and Contact Phenomena for Elastic Plates: A Review

Muradova

Stavroulakis

2020

Mathematics

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A review of mathematical models for elastic plates with buckling and contact phenomena is provided. The state of the art in this domain is presented. Buckling effects are discussed on an example of a system of nonlinear partial differential equations, describing large deflections of the plate. Unilateral contact problems with buckling, including models for plates, resting on elastic foundations, and contact models for delaminated composite plates, are formulated. Dynamic nonlinear equations for elastic plates, which possess buckling and contact effects are also presented. Most commonly used boundary and initial conditions are set up. The advantages and disadvantages of analytical, semi-analytical, and numerical techniques for the buckling and contact problems are discussed. The corresponding references are given.

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“…Wang et al (2017) considered an arcshaped crack lying along with the interface of a through-thickness circular elastic inhomogeneity in an isotropic laminated thin plate. Tiwari et al (2019) performed free vibration analysis of composite beams and plates with delaminations by using 3d degenerated element method. They considered four delamination interfaces and sizes to measure the delamination effects on the natural frequencies of composite beams and plates having single or multiple delaminations.…”

Section: Introductionmentioning

confidence: 99%

Location-based effect of decomposition on laminated curved plate structures

Gönenli

Daş

2021

Lat. Am. j. solids struct.

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Free Vibration Analysis of Delaminated Composite Plate Using 3D Degenerated Element

Cited by 18 publications

References 32 publications

Aeroelastic control of delaminated variable angle tow laminated composite plate using piezoelectric patches

Aeroelastic control of delaminated variable angle tow laminated composite plate using piezoelectric patches

Mathematical Models with Buckling and Contact Phenomena for Elastic Plates: A Review

Location-based effect of decomposition on laminated curved plate structures

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