Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Cyclic variation of the energy release rate with the minimum and maximum energy release rates used for determining the load ratio, R

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Typical fatigue crack growth curve

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Typical fatigue crack onset curve

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Schematic representation of the influence of the mixed-mode ratio in delamination onset (a) and propagation (b) curves

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Schematic representation of the variation of the Paris law coefficient m as a function of the mixed-mode ratio (qualitative representation from the data presented in Refs. [39,40,49] for carbon/epoxy laminates)

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Schematic representation based on the results reported in Ref. [40] of the influence of the mixed-mode ratio in delamination onset (a) and propagation (b) curves taking into account the nonmonotonic variation of the Paris law coefficients and the independence of the fatigue threshold Gth with the mixed-mode ratio

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Schematic representation of the influence of the load ratio in delamination onset (a) and propagation (b) curves. Subscripts 1 and 2 refer to two different loading conditions with different load ratios

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Schematic representation of the influence of matrix toughness in delamination onset (a) and propagation (b) curves

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Comparison between the fatigue crack propagation curves given by a model capturing the entire propagation curve and a Paris' law enclosed by the threshold energy release rate and the fracture toughness

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Exponential and bilinear equivalent one dimensional cohesive laws

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Propagation damage model approaches exemplified by a moment loaded DCB specimen. Left: loading–unloading hysteresis damage model. Right: Envelope load damage model.

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Sketch of the cohesive zone and damage distribution, (a) damage distribution in the DPZ before fatigue damage, (b) after fatigue damage, and (c) after static equilibrium is obtained

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Equivalent one dimensional bilinear law with a stiffness degrading damage parameter

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Equivalent one dimensional bilinear law with a traction degrading damage parameter

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Equivalent one dimensional bilinear law with an onset traction degrading damage parameter

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Cylinder model for testing performance of envelope load damage models [132]. M is the applied moment, r is the cylinder radius, θ is the angle of rotation, and Δl is the distance between spring elements.

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Bilinear cohesive law for loading–unloading hysteresis models with a predefined quasi-static cohesive law. The subscripts on the symbols indicate the cycle number.

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Cohesive law for initiation and propagation simulation. The active domain for the initiation model and propagation model are shown.

Date of download: 11/15/2017 Copyright © ASME. All rights reserved. From: Delamination Under Fatigue Loads in Composite Laminates: A Review on the Observed Phenomenology and Computational Methods Appl. Mech. Rev. 2014;66(6):060803-060803-24. doi:10.1115/1.4027647 Figure Legend: Loading–unloading hysteresis model for initiation of delamination [115]