Orthotropic Softening Material

Constitutive Law

This MPM Material is an orthotropic, elastic material, but once it fails, it develops anisotropic damage. It will remain orthotropic, but properties in some dirrections will change. The material is available only in OSParticulas and still in development. The constitutive law for this material is

      [math]\displaystyle{ \mathbf{\sigma} = (\mathbf{I} - \mathbf{D}) \mathbf{C}( \mathbf{\varepsilon}- \mathbf{\varepsilon}_{res}) }[/math]

where C is stiffness tensor for the underlying orthotopic material and D is an anisotropic 4^th rank damage tensor appropriate for damage in orthotropic materials, and [math]\displaystyle{ \mathbf{\varepsilon}_{res} }[/math] is any residual strain (such as thermal or solvent induced strains).

The MPM implementation of softening isotropic materials is described in Nairn, Hammerquist, and Aimene This extension to orthotropic materials will be in a future publication.

Damage Process

The current implementation limits crack formation such that the crack normal is normal to a symmetry direction of the material. This approach means cracks will normal in tghe x, y, or z direction of the material axes (these axes need not align with analysis axes). Crack growth in material symmetry directions within these two planes suggest a material defined by six cracking modse:

1. XY - for crack normal in x direction propagating in the y direction.
2. XZ - for crack normal in x direction propagating in the z direction.
3. YZ - for crack normal in y direction propagating in the x direction.
4. YZ - for crack normal in y direction propagating in the z direction.
5. ZX - for crack normal in z direction propagating in the x direction.
6. ZY - for crack normal in z direction propagating in the y direction.

In other words, the first letter is the normal to the crack plane while the second is the crack propagation direction within that plane. Each of these crack paths may be loaded in tension (mode I) or shear (mode II) leading to 12 toughness values. This material seeks to model all these crack options. Because a material point is either failed or not failed, it is not possible to separate the two mode I paths in any. We are thus left with three mode I properties and six mode II properties that depend on the crack normal

1. Crack normal in the x direction
   • Mode I: initiation at sigmaXXc, toughness G_XX,c^(I)
   • Mode II: for propagation in y direction, initiation at tauXY-Yc, toughness G_XY-Y,c^(I)
   • Mode II: for propagation in z direction, initiation at tauXZ-Zc, toughness G_XZ-Z,c^(I)
2. Crack normal in the y direction
   • Mode I: initiation at sigmaYYc, toughness G_YY,c^(I)
   • Mode II: for propagation in x direction, initiation at tauXY-Xc, toughness G_XY-X,c^(I)
   • Mode II: for propagation in z direction, initiation at tauYZ-Zc, toughness G_YZ-Z,c^(I)
3. Crack normal in the z direction
   • Mode I: initiation at sigmaZZc, toughness G_ZZ,c^(I)
   • Mode II: for propagation in x direction, initiation at tauXZ-Xc, toughness G_XZ-X,c^(I)
   • Mode II: for propagation in y direction, initiation at tauYZ-Yc, toughness G_YZ-Y,c^(I)

Damage Initiation and Propagation

Damage initiation is controlled by attaching a damage initiation law to the material. These laws define a failure envelop. Once the response reaches the envelop, the damage process is initiated and the normal to the crack plane is calculated depending on type of failure. The normal is needed to find the anisotropic D tensor (which involves rotating analysis into the crack axis system where the x axis is aligned with the crack normal). The only damage surface currently allowed for an orthotropic softening material is the OrthoFailure initiation law. Damage propagation and evolution is determined by softening laws laws to predict degradation of normal and shear tractions across the crack plane.

Full definition of an orthotopic material requires specification of a strength and a softening law corresponding to each of the nine modeled crack propagation modes described in the previous section. Note that the six shear models indicate a shear plane with two indices following by a second index into crack direction. For example, tauXY-Xc is the strength to initiate failure by shear in the X-Y plane and that shear failure cases a crack in the x direction or a crack with normal in the y direction. The corresponding tauXY-Yc is failure in the same plane but resulting in a crack parallel to the y direction or a crack normal in the x direction. For X-Y shear loading of a given material, the shear crack formed will allows have its orientation defined by whichever shear strength is lower (min(tauXY-Xc,tauXY-Yc)). This, the large shear value has no affect on shear failure, but still can affect damage evolution. For example, if tauXY-Xc < tauXY-Yc, all shear cracks will have normal in the y direction, but if tensile causes a crack with normal in the x direction, the value of tauXY-Yc will control subsequent shear damage evolution on that crack's surface. Similarly, shear failure in X-Z and Y-Z planes are controlled by two other pairs of shear strengths.

In brief, this material models crack initiation and propagation through damage mechanics. The softening law properties tie the damage mechanics to toughness properties for the material. The scheme can handle all model failure modes, interacting cracks (which become interacting damage zones), and 3D cracks. The damage evolves during a simulation, but, if desired, predamage on any particle at the start of a simulation can be set using initial particle damage using particle boundary conditions.

Material Properties

When the material is undamaged, its response is identical to properties entered for the underlying transversely isotropic material. Once those are specified, you have to attach one damage initiation law and five softening laws, and all properties needed by those laws. These properties determine how the material responds after initiates and propagates damage.

Property	Description	Units	Default
(Orthotropic Properties)	Enter all properties needed to define the underlying orthotropic material response	varies	varies
Initiation	Attach damage initiation law by name or ID that is compatible with this material. Once attached, enter all required strength properties for that law.	none	OrthoFailure
SofteningXX	Attach a softening law (by name or ID) for propagation of a tensile damage for a crack with normal in the x direction. Once attached, enter all required properties for that law by prefacing each property with "XX-".	none	Linear
SofteningYY	Attach a softening law (by name or ID) ffor propagation of a tensile damage for a crack with normal in the y direction. Once attached, enter all required properties for that law by prefacing each property with "YY-".	none	Linear
SofteningZZ	Attach a softening law (by name or ID) for propagation of a tensile damage for a crack with normal in the z direction. Once attached, enter all required properties for that law by prefacing each property with "ZZ-".	none	Linear
SofteningXYX	Attach a softening law (by name or ID) for propagation of shear damage for crack in with normal y direction caused by shear stress in the x-y plane. Once attached, enter all required properties for that law by prefacing each property with "XYX-".	none	Linear
SofteningXYY	Attach a softening law (by name or ID) for propagation of shear damage for crack in with normal x direction caused by shear stress in the x-y plane. Once attached, enter all required properties for that law by prefacing each property with "XYY-".	none	Linear
SofteningXZX	Attach a softening law (by name or ID) for propagation of shear damage for crack in with normal z direction caused by shear stress in the x-z plane. Once attached, enter all required properties for that law by prefacing each property with "XZX-".	none	Linear
SofteningXZZ	Attach a softening law (by name or ID) for propagation of shear damage for crack in with normal x direction caused by shear stress in the x-z plane. Once attached, enter all required properties for that law by prefacing each property with "XZZ-".	none	Linear
SofteningYZY	Attach a softening law (by name or ID) for propagation of shear damage for crack in with normal z direction caused by shear stress in the y-z plane. Once attached, enter all required properties for that law by prefacing each property with "YZY-".	none	Linear
SofteningYZZ	Attach a softening law (by name or ID) for propagation of shear damage for crack in with normal y direction caused by shear stress in the y-z plane. Once attached, enter all required properties for that law by prefacing each property with "YZZ-".	none	Linear
shearFailureSurface	Select failure surface assumed when modeling shear damage in 3D calculations. Use 1 for an elliptical failure criterion based on current degraded shear strengths. Use 0 for a rectangular failure surface that encloses the elliptical failure criterion. The elliptical surface is preferred, but rectangular is more efficient.	none	1
coefVariation	This property assigns a coefficient of variation to failure properties. The property that is affected is determined by the coefVariationMode parameter. Each particle's relative property is set at the start of the simulation to have the same Gaussian distribution of values about their means, but will have no spatial correlations. A better approach to stochastic modeling would use Gaussian random fields with spatial correlation, but the feature is not yet implemented.	none	0
coefVariationMode	The options are 1 = vary only strength, 2 = vary only toughness, and 3 = vary strength and toughness. Note that strength, toughness, and critical crack opening displacement (COD) are interrelated. Option 1 means COD will increase to keep toughness constant; 2 means COD will decrease to keep strength constant; 3 means COD will remain constant.	none	1
coeff	coefficient of friction for post-decohesion contact (default is 0 or frictionless) (experimental implementation in development in OSParticulas only)	none	0
(other)	Properties common to all materials	varies	varies

History Variables

This material stores several history variables that track the extent of the damage and orientation of the damage plane:

1. 0, 0.75, 0.8, 0.85, 0.95, 1.05, 1.15, 1.25, or 1 higher than previous 7 to indicate undamaged (0), damage propagation (0.75, 0.8, 0.85, 0.95, 1.05, 1.15, 1.25), or post failure (decohesion) state of the particle. The specific values indicate the failure mode that initiated the damage:
   • 0.75, 1.25, 1.75, 2.25: Transverse Tension
     • 0.75, 1.75: Material axial direction along z axis in the crack axis system
     • 1.25, 2.25: Material axial direction along y axis in the crack axis system
   • 0.95, 1.95: Axial Tension
     • Material axial direction along x axis in the crack axis system
   • 0.80, 1.15, 1.80, 2.15: Axial Shear
     • 0.80, 1.80: Material axial direction along z axis in the crack axis system
     • 1.15, 2.15: Material axial direction along y axis in the crack axis system
   • 1.05, 2.05: Transverse Shear
     • Material axial direction along x axis in the crack axis system
   • 0.85, 1.85: Rolling Shear (or shear failure in isotropic plane)
     • Material axial direction along z axis in the crack axis system
2. δ_n or the maximum normal cracking strain.
3. δ_xy or the maximum x-y shear cracking strain.
4. δ_xz or the maximum x-z cracking strain (zero for 2D).
5. d_n or damage variable for normal loading. It varies from 0 to 1 where 1 is complete damage or failure.
6. d_xy or damage variable for x-y shear loading. It varies from 0 to 1 where 1 is complete damage or failure.
7. d_xz or damage variable for x-z shear loading. It varies from 0 to 1 where 1 is complete damage or failure (zero for 2D).
8. For 2D it is cos(θ), but for 3D it is Euler angle α.
9. For 2D it is sin(θ), but for 3D it is Euler angle β.
10. For 2D it is not used, but for 3D it is Euler angle γ.
11. A_c/V_p where A_c is crack area within the particle and V_p is particle volume.
12. Relative strength derived at the start by coefVariation and coefVariationMode properties.
13. Relative toughness derived at the start by coefVariation and coefVariationMode properties.

Variables 8-10 define the normal to the damage crack plane. For 2D, θ is the counter clockwise angle from the x axis to the crack normal. For 3D, (α, β, γ) are the three Euler angles for the normal direction using a Z-Y-Z rotation scheme. You can use the damagenormal archiving option to save enough information for plotting the normal. Although damaged normal is a unit vector, it is archived with magnitude equal to A_c/V_p (which gets another history variable archived and the value is used for some visualization options).

This material also tracks the cracking strain which can be saved by using the plasticstrain archiving option. The strain is archived in the global axis system. If you also archive the damagenormal, you will be able to plot a vector along the crack-opening displacement vector.

Examples

This example can be a starting point for modeling of wood

 Material "wood","Douglas fir","OrthoSoftening"
   rho 0.5
   largeRotation 1
   Initiation "OrthoFailure"
   strengthCoefVariation 0.3
   SofteningAI Linear
   SofteningAII Linear
   SofteningTII Linear
   SofteningI Linear
   SofteningI Linear
   AI-Gc 1200
   AII-Gc 600
   TII-Gc 800
   I-Gc 200
   II-Gc 400
 Done