Numerical and experimental investigations of S-Glass/Polyester composite laminate plate under low energy impact

Abstract The paper presents the mixed-mode delamination response of laminate plate made of two sublaminates. To this purpose a sliding load mode of delamination is proposed as failure model. A quasistatic rate-independent delamination problem of laminate plates with a finite thickness is considered. A rate-independent delamination model for a laminated Kirchhoff-Love plate is obtained. The failure model is implemented in ANSYS code to calculate the mixed-mode delamination response as energy release rate along the lamination front.

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Development of Energy Finite Element Analysis in Vibration Analysis of Composite Laminate Plate Structures

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.470.1020 ◽

2013 ◽

Vol 470 ◽

pp. 1020-1023

Author(s):

Yang Yang ◽

Xi Liang Chen ◽

Wen Wu Zhang

Keyword(s):

Finite Element Analysis ◽

Finite Element ◽

Energy Density ◽

Vibration Analysis ◽

Composite Laminate ◽

Laminate Plate ◽

Element Analysis ◽

Plate Structure ◽

Composite Laminate Plate ◽

Energy Finite Element Analysis

The high frequency vibration analysis of a composite laminate plate structure subjected to impact loads was investigated by using method of energy finite element analysis (EFEA). The time and space averaged energy density was used as the primary variable to form the governing differential equations. The multilayer laminate plate is simplified to be equivalent isotropic plate using the average concept, such as the average damping loss factor and the average group speed. The global system of EFEA equations can be solved numerically and the energy density distribution within the whole system can then be obtained. The EFEA numerical results for composite laminate plate structure were validated through comparison with those of very dense conventional finite element analysis (FEA).

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Investigations of Bending Singularity Orders in a V-notched Composite Laminate Plate Based on the Ressiner-Mindlin Theory

MATEC Web of Conferences ◽

10.1051/matecconf/201815101001 ◽

2018 ◽

Vol 151 ◽

pp. 01001

Author(s):

Chung-De Chen

Keyword(s):

Eigenfunction Expansion ◽

Composite Laminate ◽

Laminate Plate ◽

Expansion Method ◽

Material Anisotropy ◽

Free Surfaces ◽

Eigenfunction Expansion Method ◽

Composite Laminate Plate ◽

Material Orientation ◽

Singularity Order

In this paper, the bending singularity at the apex of a V-notched composite laminate plate is investigated. The anisotropy of the laminate is modeled by the Stroh formalism. Based on the eigenfunction expansion method, the bending singularity orders can be determined by solving an eigenvalue problem numerically. The singularity orders depend on the plate angle, material orientation, material anisotropy and the laminate stacking sequence. The comparison cases show that the material orientation should avoid in order to reduce the bending singularity. The layers near the free surfaces have more significant effects on the singularity order. The findings presented in this paper are helpful in the design of the composite laminate with V-notch.

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