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).

This CDM model has been developed specifically to model AP-PLY laminates containing through thickness fiber connectivity. The complete numerical methodology is documented in: Tensile response of AP-PLY composites: A multiscale experimental and numerical study. The CDM model 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].

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

• 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.

Rutger Kok
PhD Candidate
email : [email protected]

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

[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