*HEADING
 A one element (SC6R) input deck to test composite damage model
 testing effect of fiber orientation (0 degree: fiber compression)
*PREPRINT,ECHO=YES,HISTORY=YES
**--------------------------------------------- Part1
*PART,NAME=PART-1
  *NODE
   1,  0.0, 0.0
   2,  1.
   3,  1., 1.
   4,  0.0, 1.
   5,  0.0, 0.0, 1.0
   6,  1.0, 0.0, 1.0
   7,  1.0, 1.0, 1.0
   8,  0.0, 1.0, 1.0
  *ELEMENT,TYPE=SC6R
   1, 1,2,4,5,6,8
   2, 2,3,4,6,7,8
  *ELSET,ELSET=EA
   1,2
  *SHELL SECTION,ELSET=EA,MATERIAL=GLASS_EPOXY,ORIENT=RECT
   1.0
  *NSET,NSET=fix1
   1,4,5,8 
  *NSET,NSET=fix2
   1,2,5,6
  *NSET,NSET=fix3
   1,2,3,4
  *nset, nset=move
   2,3,6,7
  *ORIENTATION,NAME=RECT
   1.0, 0.0, 0.0, 0.0, 1.0, 0.0
   3,0.0
*END PART
**--------------------------------------------- Assembly-1
*ASSEMBLY,NAME=ASSEMBLY-1
*INSTANCE,NAME=PART-1-1,PART=PART-1
*END INSTANCE
*END ASSEMBLY
**--------------------------------------------- End Assembly
*MATERIAL,NAME=GLASS_EPOXY
*ELASTIC,TYPE=LAMINA
 53.8e9,17.9e9,0.25,8.96e9,8.96e9,6.88e9
**<E11>,<E22>,<nu12>,<G12>,<G13>,<G23>
*DAMAGE INITIATION,CRITERION=HASHIN,ALPHA=0.0
 1034e6,1034e6,27.6e6,138e6,41.4e6,69e6
** <X_T>,<X_C>,<Y_T>,<Y_C>,<S_L>,<S_T>
*DAMAGE EVOLUTION, TYPE=ENERGY, SOFTENING=LINEAR
 20e6,20e6,4.0e4,1.0e6
*STEP,INC=200
 SMALL DISPLACEMENT ANALYSIS
*STATIC
 0.0001,0.01,,0.0002
*BOUNDARY
 ASSEMBLY-1.PART-1-1.move, 1,1, -0.1
 ASSEMBLY-1.PART-1-1.fix1, 1,1
 ASSEMBLY-1.PART-1-1.fix2, 2,2
 ASSEMBLY-1.PART-1-1.fix3, 3,3
*OUTPUT,FIELD,FREQ=100
*ELEMENT OUTPUT
 E,
 DAMAGEFC,
 DAMAGESHR,
*NODE OUTPUT
 U,
*OUTPUT,HISTORY
*ELEMENT OUTPUT,ELSET=PART-1-1.EA
 ELDMD,
 HSNFCCRT,
 S,
 E,
 DAMAGEFC,
 DAMAGESHR,
*EL PRINT
 HSNFCCRT
*END STEP