NOTE: This CDM routine is working for single element models (i.e. it passes single element verification tests), but is highly unstable for multi-element models. If you spot a bug or any other inconsistency let me know (contact details below).
3D Continuum Damage Mechanics VUMAT for Composite Materials
Explicit material subroutine (VUMAT) implementing a continuum damage mechanics (CDM) model for composite materials in Abaqus (in fixed format Fortran 77).
Summary
The continuum damage mechanics model implemented in this subroutine is based on the work of several authors. Failure stresses are calculated according to the three-dimensional failure criteria developed by Catalanotti et al. [1]. Damage evolution is adapted from the work of Maimi et al. [2][3] and Tan et al. [4][5].
The verification directory contains the input files required to run single-element simulations that verify the model correctly predicts the failure stress and energy dissipation for different types of loading.
The examples directory contains the input files required to run a number of simple simulations illustrating the flexibility of the model.
Usage
To run a simulation using subroutines your Abaqus installation must be linked with a Fortran compiler and compatible Visual Studio installation, see:
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
XT = tensile strength fiber direction
XC = compressive strength fiber direction
YTis = in-situ tensile strength transverse direction
YCis = in-situ compressive strength transverse direction
SLis = in-situ longitudinal shear strength
STis = in-situ transverse shear strength
ηL = shear friction coefficient longitudinal direction
α0 = failure plane angle pure transverse compression
G1+ = tensile fracture toughness fiber direction
G1- = compressive fracture toughness fiber direction
G2+ = tensile fracture toughness transverse direction
G6 = shear fracture toughness
List of Fortran source code
- composite_cdm.for : Implementation of CDM model in fixed format Fortran 77 (compatible with all Abaqus installations)
List of Verification Models
- Tension_11 : Pure tension in fiber direction
- Tension_22 : Pure tension in transverse direction
- Compression_11 : Pure compression in fiber direction
- Shear_12 : Shear in the 12 direction
- Shear_23 : Shear in the 23 direction
List of Example Models
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] G. Catalanotti, P.P. Camanho, A.T. Marques
Three-dimensional failure criteria for fiber-reinforced laminates
Composite Structures 95 (2013) 63–79
http://dx.doi.org/10.1016/j.compstruct.2012.07.016
[2] 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
[3] 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
[4] 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
[5] B. G. Falzon, H. Liu, and W. Tan
Comment on ‘A tensorial based progressive damage model for fibre reinforced polymers’
Composite Structures 176 (2017) 877–882.
http://doi.org/10.1016/j.compstruct.2017.06.011
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