/ANIM/SHELL/IDPLY/DAMA

Format

/ANIM/SHELL/IDPLY/DAMA/Keyword5/Keyword6

Definitions

Comments

1. Ply ID number is prop_ID from /PROP/TYPE19 (PLY)/prop_ID or ply_ID from /PLY/ply_ID.
2. For fully integrated BATOZ shells, I_shell=12, the value output is the maximum value of the in-plane Gauss points for a particular through the thickness integration point.
3. This applies only to failure criteria defined with /FAIL keywords. Failure defined inside material laws (/MAT/GURSON) is currently not available.
4. The damage value, D is the maximum value of all failure criteria of the model. The damage value which is displayed is the maximum damage value over time.

   In case of composite shell element property TYPE51, the damage value for one ply is computed as the maximum value over the all integration points of its ply.

   (1)

   $$D(T)={\max }_{t\le T}\left(D(t)\right)$$
5. The damage value, D is 0 ≤ D ≤ 1. The status for fracture is:

   Free, if 0 ≤ D < 1

   Failure, if D = 1

6. D is computed for every failure criteria as follows:
   • Strain based failure (/FAIL/BIQUAD)(2)
     $$D={\displaystyle \sum \frac{\text{Δ}{\epsilon }_p}{{\epsilon }_f}}$$
   • Johnson-Cook failure (/FAIL/JOHNSON) (3)
     $$D=\sum \frac{\mathrm{\text{Δ}}{\varepsilon }_p}{{\varepsilon }_f}$$
   • Tuler-Butcher failure (/FAIL/TBUTCHER) (4)
     $$D=\frac{{\underset{0}{\overset{t}{\int }}\left(\sigma -{\sigma }_r\right)}^{\lambda }dt}{K}$$
   • Wilkins failure (/FAIL/WILKINS)(5)
     $$D=\frac{{\displaystyle \int W_1{W}_{2}d{\epsilon }_p}}{D_f}$$
   • FLD failure (/FAIL/FLD) (6)
     $$D=\underset{time}{Max}\left(\frac{{\epsilon }_{major}}{{\epsilon }_{\lim }}\right)$$
   Where,

   ${\epsilon }_{\lim }$

   Strain limit from FLD function

   
   
   Figure 1.

   • BAO-XUE-Wierzbicki failure (/FAIL/WIERZBICKI)(7)
     $$D={\displaystyle \sum \frac{\text{Δ}{\epsilon }_p}{{\overline{\epsilon }}_f}}$$
   • Strain failure model (/FAIL/TENSSTRAIN)(8)
     $$D=\underset{\mathit{time}}{\mathit{Max}}\left(\frac{{\varepsilon }_1-{\varepsilon }_{t_1}}{{\varepsilon }_{t_2}-{\varepsilon }_{t_1}}\right)$$
   • Strain failure model (/FAIL/FABRIC)(9)
     $$D=Max\left(\frac{{\epsilon }_1-{\epsilon }_{f1}}{{\epsilon }_{r1}-{\epsilon }_{f1}},\frac{{\epsilon }_2-{\epsilon }_{f2}}{{\epsilon }_{r2}-{\epsilon }_{f2}}\right)$$
   • Energy density failure model (/FAIL/ENERGY):(10)
     $$D=\underset{\mathit{time}}{\mathit{Max}}\left(\frac{E-E_1}{E_2-E_1}\right)$$
   • Chang failure (/FAIL/CHANG)
     The maximum damage for different failure mode: (11)

     $$D=\mathit{Max}\left(e_f{}^2,e_c{}^2,e_m{}^2,e_d{}^2\right)$$
   • Hashin Composite failure (/FAIL/HASHIN)

     The maximum damage for different failure mode

     For uni-directional lamina model:(12)

     $$D=Max\left(F_1,F_2,F_3,F_4,F_5\right)$$
     For fabric lamina model:(13)

     $$D=Max\left(F_1,F_2,F_3,F_4,F_5,F_6,F_7\right)$$
   • Puck Composite failure (/FAIL/PUCK)
     The maximum damage for different failure mode:(14)

     $$D=\mathit{Max}\left(e_f(\mathit{tensile}),e_f(\mathit{compression}),e_f(\mathit{ModeA}),e_f(\mathit{ModeB}),e_f(\mathit{ModeC})\right)$$
   • Strain Failure Model with dependence on Lode angle (/FAIL/TAB1)(15)
     $$D=\frac{\sum \mathrm{\text{Δ}}D}{D_{crit}}$$
   • NXT Failure Model (/FAIL/NXT)(16)
     $$D=\frac{{\lambda }_f}{2}$$