在 Fortran ( Abaqus Explicit VUMAT) 中实现的复合材料 3D 连续介质损伤力学模型

__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 **X_T** = tensile strength fiber direction **X_C** = compressive strength fiber direction **Y_T^is** = in-situ tensile strength transverse direction **Y_C^is** = in-situ compressive strength transverse direction **S_L^is** = in-situ longitudinal shear strength **S_T^is** = in-situ transverse shear strength **η_L** = shear friction coefficient longitudinal direction **α₀** = failure plane angle pure transverse compression **G₁₊** = tensile fracture toughness fiber direction **G_1-** = 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 - **placeholder** : TBD *** Rutger Kok PhD Candidate email : rutger.kok@ed.ac.uk 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