scholarly journals Post-buckling delamination propagation analysis using interface element with de-cohesive constitutive law

2011 ◽  
Vol 10 ◽  
pp. 1797-1802 ◽  
Author(s):  
Bijan Mohammadi ◽  
Farhad Shahabi ◽  
S.A.M. Ghannadpou
Keyword(s):  
Constitutive Law ◽  
Interface Element ◽  
Propagation Analysis ◽  
Post Buckling ◽  
Buckling Delamination ◽  
Delamination Propagation

Large Deformation and Failure of Thin-Walled Film at the Post-Buckling Delamination

2013 ◽  
Vol 577-578 ◽  
pp. 497-500 ◽  
Author(s):  
Vitalijs Pavelko ◽  
Igors Pavelko ◽  
Maxim Smolyaninov
Keyword(s):  
Large Deformation ◽  
Strain Energy ◽  
Layered Composite ◽  
Progressive Damage ◽  
Deformation And Failure ◽  
Post Buckling ◽  
1D Model ◽  
Buckling Delamination ◽  
Thin Walled ◽  
Delamination Propagation

An accurate 1D model of post-buckling deformation of a thin sub-laminate of layered composite is develloped using nonlinead theory of slender plate. The strain energy realize rate at delamination propagation is obtained via the elliptical integrals. A model of fracture buckled sub-laminate is implemented and used for general analysis of progressive damage of composite

Multiple Delaminations Growth in Composite Laminates under Compressive Cyclic Loading in Post-Buckling

2012 ◽  
Vol 225 ◽  
pp. 195-200
Author(s):  
Hossein Hosseini-Toudeshky ◽  
M. Saeed Goodarzi ◽  
Bijan Mohammadi
Keyword(s):  
Cyclic Loading ◽  
Cohesive Zone ◽  
Composite Laminates ◽  
Mixed Mode ◽  
Composite Laminate ◽  
Constitutive Law ◽  
Interface Element ◽  
Delamination Growth ◽  
Post Buckling ◽  
Interface Layers

Due to discontinuity of mechanical properties in composite laminates, failure occurs in different damage mechanisms. Delamination growth of adjacent layers is a major failure mechanism in laminates with various layup configurations. Pre existing delamination may initiate in composite laminate before use, due to impact in assembly and fabrication process. Cyclic compressive loading may cause delamination growth due to both post-bucking behavior and fatigue nature of loading. In this paper, a 3D mixed-mode interface element model has been developed to simulate the growth of multiple delaminations under compressive cyclic loading. For this purpose, the presented model should be able to handle the geometry nonlinearity of post-buckling and material nonlinearity of cohesive zone constitutive law under cyclic loading at interfaces. Because of mixed-mode condition of stress field at the delamination-front of post-buckled laminates, a mixed-mode bilinear constitutive law has been used as user material in this model. Paris Law has been used to relate the energy release rate to the fatigue crack growth in cohesive zone. A composite laminate with pre-existing delamination under buckling load, available from the literature has been reproduced with the present approach. Finally, laminates containing multiple delaminations in various interface layers have been analyzed under compressive fatigue loading. It is shown that the pre-existing delamination with more depth from the surface of laminate causes more initial static and fatigue delamination growth rate.

Coupling of Continuum Damage Mechanics with De-Cohesive Element for Delamination Analysis in Laminated Composites

2010 ◽  
Vol 123-125 ◽  
pp. 527-530
Author(s):  
Hossein Hosseini-Toudeshky ◽  
Bijan Mohammadi
Keyword(s):  
Mesh Generation ◽  
Composite Laminates ◽  
Damage Mechanics ◽  
Plate Theory ◽  
Continuum Damage Mechanics ◽  
Constitutive Law ◽  
Interface Element ◽  
Continuum Damage ◽  
Interface Modeling ◽  
Edge Delamination

To predict the progressive damages including the large delamination growth in composite laminates, a new interface de-cohesive constitutive law is developed which is compatible with 3D continuum damage mechanics (CDM). To avoid the difficulties of 3D mesh generation and 3D interface modeling between the layers, the interface element is implemented in the Reddy’s full layer-wise plate theory. An angle-ply laminate is analyzed to evaluate the developed CDM+Interface procedure in edge delamination initiation and evolution at final stage of CDM damage progress.

Behavior of Thin-Film-Type Delamination of Layered Composite in Post-Buckling

2013 ◽  
Vol 774-776 ◽  
pp. 1312-1321 ◽  
Author(s):  
Vitalijs Pavelko
Keyword(s):  
Compressive Force ◽  
Layered Composite ◽  
Stress And Strain ◽  
Elastic Plates ◽  
Post Buckling ◽  
Complete Elliptic Integrals ◽  
Analysis Of Stability ◽  
Delamination Propagation ◽  
State Stress ◽  
Buckled State

A revision of the basic assumptions those are usually used in the analysis of stability of thin delaminated layer and delamination propagation in a compressed composite is presented in this paper. For this purpose, the theory of flexible elastic plates with large displacements was used. As a result the compressive force and the total longitudinal strain of sub-laminate are expressed in terms of complete elliptic integrals, which uniquely identify the buckled shape of sub-laminate, the effect of buckling on the compression strain and increment of the compressive force in the buckled state. Stress and strain, as well as the strength of the buckled sub-laminate in the dangerous cross-section were also analyzed. The results of the general analysis of delamination propagation and its compression-bending destruction in the buckled state allow to define the basic regularities of the damage behavior of compressed layered composite.

Fatigue Delamination Analysis of Composite Laminates with a Central Hole Using Interface Elements

2011 ◽  
Vol 471-472 ◽  
pp. 568-571
Author(s):  
Hossein Hosseini-Toudeshky ◽  
A. Jasemzadeh ◽  
Bijan Mohammadi
Keyword(s):  
Cyclic Loading ◽  
Composite Laminates ◽  
Mixed Mode ◽  
Composite Laminate ◽  
Constitutive Law ◽  
Central Hole ◽  
Interface Element ◽  
Interface Elements

In this paper a solid like interface element along with a fatigue constitutive law is used to study the damage behaviour of holed composite laminates under cyclic loading. For this purpose a user element routine and a material routine was developed include the interface element and to handle the formulation of progressive fatigue damages. The developed procedure is used to predict delamination initiation and growth in mixed-mode condition for a typical composite laminate. The obtained results for damage and stresses are compared with the available results in the literature.

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