Mohammad-Abazari / composite_cdm_ap_ply

Continuum damage mechanics framework for AP-PLY composites implemented as an Abaqus VUMAT subroutine.

3D Continuum Damage Mechanics VUMAT for AP-PLY Composite Materials

Explicit material subroutine (VUMAT) implementing a continuum damage mechanics (CDM) model for Adavanced Placed Ply (AP-PLY) composite materials in Abaqus (in fixed format Fortran 77).

Summary

This CDM model has been developed specifically to model AP-PLY laminates containing through thickness fiber connectivity. The complete numerical methodology will be documented in an as yet to be published journal paper. The CDM model implemented in this subroutine is an amalgamation of the work of several authors. Failure criteria are adopted from the work of Tan et al. [1] and Shah et al. [2]. Damage evolution is defined according to the methodlogies proposed in the work of Maimi et al. [3][4] and Shah et al. [2].

Usage

To run a simulation using subroutines your Abaqus installation must be linked with a Fortran compiler and compatible Visual Studio installation.

The model requires the following material properties to be defined in the simulation input (.inp) file:
E₁₁ = elastic modulus in the fiber direction
E₂₂= elastic modulus transverse direction (in-plane)
E₃₃ = elastic modulus transverse direction (out-of-plane)
ν₁₂ = Poisson's ratio 12 direction
ν₁₃ = Poisson's ratio 13 direction
ν₂₃ = Poisson's ratio 23 direction
G₁₂ = shear modulus 12 direction
G₁₃ = shear modulus 13 direction
G₂₃ = shear modulus 23 direction
X_T = tensile strength fiber direction
X_C = compressive strength fiber direction
Y_T^is = in-situ tensile strength transverse direction
Y_C^is = compressive strength transverse direction
Z_T^is = in-situ tensile strength through-thickness direction
Z_C^is = compressive strength through-thickness direction
S_L^is = in-situ 12 shear strength
S_R^is = in-situ 13 shear strength
S_T^is = 23 shear strength
G₁₊ = tensile fracture toughness fiber direction
G_1- = compressive fracture toughness fiber direction
G₂₊ = tensile fracture toughness transverse direction
und_angle₁ = in-plane angle undulation region constituent 1
und_angle₂ = in-plane angle undulation region constituent 2
cpt = cured ply thickness
und_length = undulation length

List of Fortran source code

• composite_cdm.for : Main CDM model script. Imports the resin_damage and rotation_matrix files.
• resin_damage.for : Implements an isotropic CDM model for pure resin regions
• rotation_matrix.for : Populates the rotation matrix for stress/strain transformation about 2 axes.

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Rutger Kok
PhD Candidate
email : [e-mail]

Institute for Infrastructure and Environment
University of Edinburgh
Thomas Bayes Road, King's Buildings, Edinburgh EH9 3FG
United Kingdom

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[1] W. Tan, B. G. Falzon, L. N. S. Chiu, and M. Price
Predicting low velocity impact damage and Compression-After-Impact (CAI) behaviour of composite laminates
Composites Part A 71 (2015) 212–226.
http://doi.org/10.1016/j.compositesa.2015.01.025

[2] S. Z. H. Shah, P. S. M. Megat-Yusoff, S. Karuppanan, R.S. Choudhry, and Z. Sajid
Multiscale damage modelling of 3D woven composites under static and impact loads
Composites Part A: Applied Science and Manufacturing 151 (2021).
https://doi.org/10.1016/j.compositesa.2021.106659

[3] P. Maimi, P.P. Camanho, J.A. Mayugo, C.G. Davila
A continuum damage model for composite laminates: Part I – Constitutive model
Mechanics of Materials 39 (2007) 897–908
http://dx.doi.org/10.1016/j.mechmat.2007.03.005

[4] P. Maimi, P.P. Camanho, J.A. Mayugo, C.G. Davila
A continuum damage model for composite laminates: Part II – Computational implementation and validation
Mechanics of Materials 39 (2007) 909–919
http://dx.doi.org/10.1016/j.mechmat.2007.03.006