scholarly journals A critical study on impact damage simulation of IM7/8552 composite laminate plate

2019 ◽  
Vol 127 ◽  
pp. 100-109 ◽  
Author(s):  
Hao Cui ◽  
Daniel Thomson ◽  
Sina Eskandari ◽  
Nik Petrinic
Keyword(s):  
Composite Laminate ◽  
Impact Damage ◽  
Laminate Plate ◽  
Critical Study ◽  
Composite Laminate Plate ◽  
Damage Simulation

scholarly journals Delamination of Composite Laminate Plate by Sliding Load Mode

2017 ◽  
Vol 17 (1) ◽  
pp. 69-72
Author(s):  
Eva Kormaníková
Keyword(s):  
Energy Release Rate ◽  
Energy Release ◽  
Release Rate ◽  
Mixed Mode ◽  
Composite Laminate ◽  
Finite Thickness ◽  
Laminate Plate ◽  
Failure Model ◽  
Composite Laminate Plate ◽  
Load Mode

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.

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

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).

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

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.

Compressive Experiment and Damage Simulation of a Composite Structure with Ply Drop-Off

2007 ◽  
Vol 334-335 ◽  
pp. 301-304
Author(s):  
Xiao Jun Shao ◽  
Zhu Feng Yue
Keyword(s):  
Mechanical Properties ◽  
Carrying Capacity ◽  
Composite Laminate ◽  
Compressive Loading ◽  
Laminate Plate ◽  
Matrix Cracking ◽  
Damage Development ◽  
User Subroutine ◽  
Fiber Matrix ◽  
Damage Simulation

Compressive experiments and finite element method (FEM) have been used to study the mechanical behavior of composite laminate with plies drop-off. A user subroutine has been implemented to ABAQUS to simulate the damage development of the laminate plate. This user subroutine has taken consideration of the mechanical properties degradation according to development of three types of damage. The load-strain curves can agree with each other between experiments and FEM. The detail of damage development of the plies drop-off composite laminate under compressive loading can be described as followed. Matrix cracking damage and fiber-matrix shearing damage occur simultaneously at first, and then fiber buckling damage initiates. Matrix cracking and fiber-matrix shearing are very dangerous to the carrying capacity of laminate and fiber buckling intensifies further this effect. The initiation and development of fiber buckling indicates that laminate loses carrying capacity at all.

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