/MAT/LAW58 (FABR_A)

Block Format Keyword This law describes a hyperelastic anisotropic fabric material. It uses an anisotropic coordinate system with an anisotropy angle, following element deformation.

The material formulation provides coupling between warp and weft directions in order to reproduce physical interaction between fibers. The shear degree of freedom is fully decoupled from the translational degrees of freedom. Optionally, nonlinear stress-strain curves for loading and unloading can be specified for warp, weft directions and in shear.

Format


(1)	(2)	(3)	(5)	(7)	(9)	(10)
/MAT/LAW58/`mat_ID`/`unit_ID` or /MAT/FABR_A/`mat_ID`/`unit_ID`
`mat_title`
$ρ_{i}$ $ρ_{i}$
`E`₁		`B`₁	`E`₂	`B`₂	`Flex`
`G`₀		`G`_T	$α_{T}$ $α_{T}$	`G`_sh		`sens_ID`
`D`_f		`D`_s	`G`_frot		`ZeroStress`
`N`₁	`N`₂	`S`₁	`S`₂	`Flex`₁	`Flex`₂

Optional lines:


(1)	(2)	(3)	(5)	(7)	(8)
`fct_ID`₁		`Fscale`₁
`fct_ID`₂		`Fscale`₂
`fct_ID`₃		`Fscale`₃
`fct_ID`₄	`fct_ID`₅	`Fscale`₄	`Fscale`₅	`fct_ID`₆	`Fscale`₆

Definition


Field	Contents	SI Unit Example
`mat_ID`	Material identifier. (Integer, maximum 10 digits)
`unit_ID`	Unit Identifier. (Integer, maximum 10 digits)
`mat_title`	Material title. (Character, maximum 100 characters)
$ρ_{i}$ $ρ_{i}$	Initial density. (Real)	$[\frac{kg}{m^{3}}]$ $[\frac{kg}{m^{3}}]$
`E`₁	Young's modulus in the warp direction. (Real)	$[Pa]$ $[Pa]$
`B`₁	Softening coefficient in the warp direction. Default = 0.00 (Real)	$[Pa]$ $[Pa]$
`E`₂	Young's modulus in the weft direction. (Real)	$[Pa]$ $[Pa]$
`B`₂	Softening coefficient in the weft direction. Default = 0.00 (Real)	$[Pa]$ $[Pa]$
`Flex`	Fiber bending modulus reduction factor. Default = 0.01 (Real)
`G`₀	Initial shear modulus. Default = G, where $G = \frac{G_{T}}{1 + \tan^{2} (α_{T})}$ $G = \frac{G_{T}}{1 + \tan^{2} (α_{T})}$ (Real)	$[Pa]$ $[Pa]$
`G`_T	Tangent shear modulus at $α = α_{T}$ $α = α_{T}$ . (Real)	$[Pa]$ $[Pa]$
$α_{T}$ $α_{T}$	Shear locking angle. (Real)	$[\deg]$ $[\deg]$
`G`_sh	Traverse shear modulus (only used with multi-layer property). Default $G_{s h} = G_{0}$ $G_{s h} = G_{0}$ (Real) If `G`₀ = 0, then $G_{s h} = \frac{G_{T}}{1 + \tan^{2} (α_{T})}$ $G_{s h} = \frac{G_{T}}{1 + \tan^{2} (α_{T})}$	$[Pa]$ $[Pa]$
`sens_ID`	Sensor identifier to activate reference geometry. 8 (Integer, maximum 10 digits)
`D`_f	Damping coefficient in the warp and weft directions (0.0 < `D`_f < 1.0). 2 Default = 0.00 (Real)
`D`_s	Friction coefficient between fibers in shear (0.0 < `D`_s < 1.0). 6 Default = 0.00 (Real)
`G`_frot	Shear friction modulus. 6 Default $G_{frot} = G_{0}$ $G_{frot} = G_{0}$ (Real) If `G`₀ = 0, then $G_{frot} = \frac{G_{T}}{1 + \tan^{2} (α_{T})}$ $G_{frot} = \frac{G_{T}}{1 + \tan^{2} (α_{T})}$ .
`ZeroStress`	Zero stress flag for initial stresses in tension and compression by using reference state geometry. 7 = 0 No stress reduction. = 1 Full stress reduction. (Real)
`N`₁	Fiber density (number of fibers per length unit) in warp direction. 2 Default = 1 (Integer)
`N`₂	Fiber density (number of fibers per length unit) in weft direction. 2 Default = 1 (Integer)
`S`₁	Straightening strain in the warp direction. 5 Default = 0.10 (Real)
`S`₂	Straightening strain in the weft direction. 5 Default = 0.10 (Real)
`Flex`₁	Fiber bending modulus reduction factor in warp direction. 5 Default = Flex (Real)
`Flex`₂	Fiber bending modulus reduction factor in weft direction. 5 Default = Flex (Real)
`fct_ID`₁	(Optional) Loading function identifier for engineering stress versus engineering strain in warp direction. 4 Default = 0 (Integer)
`Fscale`₁	(Optional) Scale factor for ordinate of function 1. Default = 1.0 (Real)	$[Pa]$ $[Pa]$
`fct_ID`₂	(Optional) Loading function identifier for engineering stress versus engineering strain in weft direction. 4 Default = 0 (Integer)
`Fscale`₂	(Optional) Scale factor for ordinate of function 2. Default = 1.0 (Real)	$[Pa]$ $[Pa]$
`fct_ID`₃	(Optional) Loading function identifier for engineering shear stress versus the anisotropy complementary angle (in degrees) between fiber directions (axes of anisotropy). 6 Default = 0 (Integer)
`Fscale`₃	(Optional) Scale factor for ordinate of function 3. Default = 1.0 (Real)	$[Pa]$ $[Pa]$
`fct_ID`₄	(Optional) Unloading function identifier for engineering stress versus engineering strain in warp direction. 4 Default = 0 (Integer)
`Fscale`₄	(Optional) Scale factor for ordinate of function 4. Default = 1.0 (Real)	$[Pa]$ $[Pa]$
`fct_ID`₅	(Optional) Unloading function identifier for engineering stress versus engineering strain in weft direction. 4 Default = 0 (Integer)
`Fscale`₅	(Optional) Scale factor for ordinate of function 5. Default = 1.0 (Real)	$[Pa]$ $[Pa]$
`fct_ID`₆	(Optional) Unloading function identifier for engineering shear stress versus the anisotropy complementary angle (in degrees) between fiber directions (axes of anisotropy). 6 Default = 0 (Integer)
`Fscale`₆	(Optional) Scale factor for ordinate of function 6. Default = 1.0 (Real)	$[Pa]$ $[Pa]$

▸Example (Fabric with parameter input)

#RADIOSS STARTER
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/UNIT/1
unit for mat
                  kg                   m                   s
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
#-  2. MATERIALS:
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/MAT/LAW58/1/1
FABRIC
#              RHO_I
               722.5
#                 E1                  B1                  E2                  B2                FLEX
           450000000                   0           450000000                   0                0.01
#                 G0                  GT              AlphaT                 Gsh           sensor_ID
                   0            10000000                  60                   0                   0
#                 Df                  Ds               GFROT                             ZERO_STRESS
                 .05                 .05                   0                                       0	 
#       N1        N2                  S1                  S2               FLEX1               FLEX2
         1         1                 .05                 .05                   0                   0
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
#ENDDATA
/END
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|

▸Example (Fabric with function input)

#RADIOSS STARTER
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/UNIT/1
unit for mat
                  kg                  mm                  ms
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
#-  2. MATERIALS:
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/MAT/LAW58/1/1
Altair test fabric LAW58
#              RHO_I
               8e-07
#                 E1                  B1                  E2                  B2                FLEX
                0.38                   0                0.38                   0                   1
#                 G0                  GT              AlphaT                 Gsh           sensor_ID
              0.0035              0.0055               7.175                   0                   1
#                 Df                  Ds               GFROT                             ZERO_STRESS
                0.00                0.00                   0                                       1	 
#       N1        N2                  S1                  S2               FLEX1               FLEX2
         1         1                   0                   0                   0                   0
#  fct_ID1                       Fscale1
       500                             1
#  fct_ID2                       Fscale2
       501                          1.07
#  fct_ID3                       Fscale3
       502                             1
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/FUNCT/500
stress-strain curve dir 1
#        Eng. strain         Eng. stress
   0.0000000000e+000                   0
   9.9503308532e-003   2.9636979188e-003
   1.9802627296e-002   5.3682944250e-003
   2.9558802242e-002   7.1312474875e-003
   3.9220713153e-002   8.7543744167e-003
   4.8790164169e-002   1.0626227281e-002
   5.8268908124e-002   1.2828957400e-002
   6.7658648474e-002   1.5214981140e-002
   7.6961041136e-002   1.7923677525e-002
   8.6177696241e-002   2.0931047458e-002
   9.5310179804e-002   2.4244941875e-002
   1.0436001532e-001   2.8050134750e-002
   1.1332868531e-001   3.2157106333e-002
   1.2221763272e-001   3.6791281562e-002
   1.3102826241e-001   4.1811352500e-002
   1.3976194238e-001   4.7185817708e-002
   1.4842000512e-001   5.3009665500e-002
/FUNCT/501
stress-strain curve dir 2
#        Eng. strain         Eng. stress
   0.0000000000e+000                   0
   9.9503308532e-003   3.7850414917e-003
   1.9802627296e-002   6.6041801875e-003
   2.9558802242e-002   8.9026150938e-003
   3.9220713153e-002   1.1200598067e-002
   4.8790164169e-002   1.3569178437e-002
   5.8268908124e-002   1.6244941225e-002
   6.7658648474e-002   1.9356706823e-002
   7.6961041136e-002   2.2930409250e-002
   8.6177696241e-002   2.7109342313e-002
   9.5310179804e-002   3.1773431250e-002
   1.0436001532e-001   3.6903321313e-002
   1.1332868531e-001   4.2590270333e-002
   1.2221763272e-001   4.8734555250e-002
   1.3102826241e-001   5.5311888000e-002
   1.3976194238e-001   6.2350489167e-002
   1.4842000512e-001   6.9690045000e-002
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/FUNCT/502
stress-strain curve dir 12
#              angle         Eng. stress
  -16.170000000e-000  -1.5741500000e-003
  -7.1750000000e-000  -4.3750000000e-004
   0.0000000000e+000   0.0000000000e+000
   7.1750000000e-000   4.3750000000e-004
   16.170000000e-000   1.5741500000e-003

#ENDDATA
/END
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|

Comments

This law is used with the properties, /PROP/TYPE16 (SH_FABR), /PROP/TYPE19 (PLY), /PROP/TYPE51, /PLY and /PROP/PCOMPP.
Fiber characterization:
- N₁ and N₂ are the number of fibers per length unit, which are used to calculate stress in both fiber directions.
- The fiber directions (warp and weft) define local axes of anisotropy. Material data is specified independently for each direction and in shear.
- Fiber damping is used to suppress instabilities as a result of elastic material behavior. The recommended value for the damping coefficient in the fiber direction D_f is 0.05.
Rules concerning input functions for the optional loading and unloading stress-strain curves.
- All tabulated input curves must be monotonically increasing. Radioss Starter will output an error message when the input is not monotonically increasing in case of wrong input.
- Case without unloading (fct_ID₄=fct_ID₅=fct_ID₆=0):
  All loading functions are optional. You may use an analytical formula or define a loading function in any direction. Tabulated and analytical behavior may be mixed in any direction.
- Case of loading / unloading with hysteresis with at least one unloading function is defined.
  - Loading functions are mandatory in all directions. Functions fct_ID₁, fct_ID₂, and fct_ID₃ must all be defined. It is not possible to mix analytical formula in loading with unloading functions.
  - Not all unloading curves need to be defined. If an unloading curve is missing in any direction, the loading and unloading will take the same path with no hysteresis.
  - If loading and unloading functions are defined, they must have strictly only one intersection point to define the hysteresis loop. The exception is the shear functions are curves in shear which must have two intersection points for negative and positive values.
  - An error message is written when input is incorrect.
Stress-strain relation in tension and compression in direction of fibres.
- When nonlinear functions are used.
  fct_ID₁, fct_ID₂ define loading and fct_ID₄, fct_ID₅ unloading behavior
  
  Figure 1.
- When parameters are used, the analytical relationships between stress and strain are defined for both loading and unloading, as:
  - $\frac{d σ}{d ε} > 0$ $\frac{d σ}{d ε} > 0$
    $σ_{i i} = E_{i} ε_{i i} - \frac{(B_{i} ε_{i i}^{2})}{2} (i = 1, 2)$ $σ_{i i} = E_{i} ε_{i i} - \frac{(B_{i} ε_{i i}^{2})}{2} (i = 1, 2)$
  - $\frac{d σ}{d ε} \leq 0$ $\frac{d σ}{d ε} \leq 0$
    $σ_{i i} = \max_{ε_{i i}} (E_{i} ε_{i i} - \frac{(B_{i} ε_{i i}^{2})}{2}) (i = 1, 2)$ $σ_{i i} = \max_{ε_{i i}} (E_{i} ε_{i i} - \frac{(B_{i} ε_{i i}^{2})}{2}) (i = 1, 2)$
  The analytical parameters are not used if the nonlinear functions (fct_ID₁, fct_ID₂, fct_ID₄ and fct_ID₅) are specified. However, the values E₁, E₂, are still required to calculate the prestress from the reference geometry and evaluate material stiffness used in contact. In such cases, E₁, E₂ should correspond to average stiffness (average slope) of the corresponding loading functions.
Initial straightening effect of the woven fabric.
This material allows you to account for the initial straightening effect of the woven fabric.

Figure 2.
- It is assumed to be softer in the tensile direction during the straightening phase. In biaxial tension there is no straightening phase and the fibers bear loads from the beginning of the loading phase.
  Use factor Flex_i to scale the E modulus or function $f_{i}$ $f_{i}$ (fct_ID₁ or fct_ID₂) in corresponding direction.
  $f_{f t_i} = F l e x_{i} \cdot f_{i}$ $f_{f t_i} = F l e x_{i} \cdot f_{i}$ (function input)
  $E_{f t} = F l e x_{i} \cdot E_{i}$ $E_{f t} = F l e x_{i} \cdot E_{i}$ (parameter input)
  
  Figure 3.
  - If the value of Flex₁ or Flex₂ is equal to zero, then the value of Flex will be used.
  - The straightening portion of the strain is given by the strains S₁ and S₂ for direction 1 and 2 correspondingly.
  - The functions fct_ID₁ and fct_ID₂ correspond to biaxial tension, where the initial straightening is not taken into account. In uniaxial tension, the straightening effect is accounted for by using Flex₁ and Flex₂ in the stress calculation. It is similar to the case when E₁ and E₂ are specified instead of the curves.
- In compression, the Young's modulus is always:
  $E = F l e x_{i} \cdot E_{i}$ $E = F l e x_{i} \cdot E_{i}$
  
  Figure 4.
Stress-strain relation in shear.
- When tabulated input is present fct_ID₃ is used for loading and fct_ID₆ for unloading.
  - If fct_ID₆ is not specified, the material is assumed to be hyperelastic, and the loading and unloading paths are the same.
  - If fct_ID₆ is given, the material shows hysteresis behavior with different path for loading and unloading in shear directions.
  - The nonlinear functions (fct_ID₃, fct_ID₆) are not mandatory. If these functions are not specified, the corresponding values of G₀, and G_T are used to calculate the stress-strain relationship of the material.
  - For function fct_ID₃, fct_ID₆, which determine loading and unloading in shear the abscissa $α$ $α$ should be set in degrees. The functions should be specified both for negative and positive values of the angle (normally the functions are symmetrical).
  - Absolute value of the angle, and its value should be less than 90 degrees, $| α | < 90^{\circ}$ $| α | < 90^{\circ}$ .
  - Loading and unloading functions should pass through point (0,0). Loading and unloading curves should have exactly one intersection point for negative angle and another intersection point for positive angle.
    
    Figure 5.
    The anisotropy complementary angle $α$ $α$ , which is equal to the difference between 90 degrees and the current angle between the anisotropy axes.
    The shear input curve can be recovered using UVAR = 3 versus arctan (UVAR = 6).
- When parameters are used to describe relation between shear stress and angle, two different shear situations could be described:
  - In plane (1 - 2) shear:
    Before shear locking angle $α \leq α_{T}$ $α \leq α_{T}$ :
    $τ = G_{0} \tan (α) - τ_{0}$ $τ = G_{0} \tan (α) - τ_{0}$
    After shear locking angle $α > α_{T}$ $α > α_{T}$ :
    $τ = G \tan (α) + G_{A} - τ_{0}$ $τ = G \tan (α) + G_{A} - τ_{0}$
    
    Figure 6.
    Where,
    
    $G_{A} = (G_{0} - G) \tan (α_{T})$ $G_{A} = (G_{0} - G) \tan (α_{T})$
    
    $G = \frac{G_{T}}{1 + \tan^{2} (α_{T})}$ $G = \frac{G_{T}}{1 + \tan^{2} (α_{T})}$
    
    $τ_{0} = G_{0} \tan (α_{0})$ $τ_{0} = G_{0} \tan (α_{0})$
    
    $α_{T}$ $α_{T}$
    
    Shear locking angle
    
    G_T
    
    Shear modulus at $α_{T}$ $α_{T}$
    
    G₀
    
    Shear modulus at $α = α_{0}$ $α = α_{0}$
  - If the G₀ = 0, then its value is calculated to avoid discontinuity of the shear modulus at $α_{T}$ $α_{T}$ : G₀ = G
  - The values of G₀ and G_T are ignored if the nonlinear functions (fct_ID₃ and fct_ID₆) are specified. However, the values G₀ is still required to calculate the prestress from the reference geometry and evaluate material stiffness used in contact. In such cases, G₀ should correspond to average stiffness (average slope) of the corresponding loading functions.
  - $α_{T}$ $α_{T}$ is an initial complementary angle, which is equal to the difference between 90 degrees and the initial angle between the anisotropy axes defined in the shell property (/PROP/TYPE16 (SH_FABR)).
    Note: Initial pre-stress exists in the fabric material if the initial angle between the fiber axes specified in the property is not equal to 90 degrees.
  - It is also possible to describe the interaction of shear stress between fibers. Use G_frot (the shear modulus) to calculate interaction shear stress ( $G_{frot} * (\dot{α})$ $G_{frot} * (\dot{α})$ ) between fibers. The friction in-plane shear stress between the fibers is calculated as $D_{s} * G_{frot} * (\dot{α})$ $D_{s} * G_{frot} * (\dot{α})$ .
  - Out-of-plane shear:
    It is possible to describe transverse shear between multi-layers (plies) with shear modulus $G_{s h}$ $G_{s h}$ .
The ZeroStress flag is used to remove initial stresses in the folded airbag. These initial stresses arise during the folding process. Numerically this pre-stress is specified through a reference airbag geometry which represents an unfolded airbag state. If ZeroStress=1, then compressive and tensile initial stresses are set to zero and then gradually increase to the actual value after deployment begins.
sens_ID is used only with ZeroStress =1 and reference airbag geometry. It activates the pre-stress based on the values output from the sensor. This is useful for airbags with time to fire > 0.
Output for post-processing:
This material uses the anisotropic coordinate system, with the angle between the material coordinate system axes (anisotropy angle) updated based on the element deformation. Special user-defined output should be used to evaluate stresses, strains, and the shear angle alpha. In the /TH/SHEL and /TH/SH3N entries in the Starter file and in /H3D/SHELL or /ANIM/SHELL in the Engine file, you should specify the following:
- /H3D/SHELL/USER/UVAR=1 or /ANIM/SHELL/USR1 - engineering stress in fiber direction 1
- /H3D/SHELL/USER/UVAR=2 or /ANIM/SHELL/USR2 - engineering stress in fiber direction 2
- /H3D/SHELL/USER/UVAR=3 or /ANIM/SHELL/USR3 - engineering stress in shear direction
- /H3D/SHELL/USER/UVAR=4 or /ANIM/SHELL/USR4 - engineering strain in fiber direction 1
- /H3D/SHELL/USER/UVAR=5 or /ANIM/SHELL/USR5 - engineering strain in fiber direction 2
- /H3D/SHELL/USER/UVAR=6 or /ANIM/SHELL/USR6 - tan( $α$ $α$ )
- /H3D/SHELL/ALPHA - Shear angle alpha of material /MAT/LAW58 in degrees.
Due to special material formulation (decoupled DOF with special interaction between fibers), the stress component does not form a stress tensor; therefore, usual tensor evaluations such as von Mises stress, principal stresses, and so on, have no meaning for the material.
Thickness is constant for material /MAT/LAW58. Flag I_thick in the property /PROP/TYPE16 is not used for this material.